AD 78-01-17
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Kawasaki Heavy Industries, Limited | KV107-II | Airworthiness Directives; KAWASAKI HEAVY INDUSTRIES, LTD Models KV-107-II and KV-107-IIA Helicopter |
| aircraft | Kawasaki Heavy Industries, Limited | KV107-IIA | Airworthiness Directives; KAWASAKI HEAVY INDUSTRIES, LTD Models KV-107-II and KV-107-IIA Helicopter |
Unsafe Condition
Fatigue cracks on the forward and aft rotor drive shafts, fatigue failure of the aft rotor transmission quill shaft, cracking in the synchronizing shaft splined adapter, cracking in the rotor pitch housing and blade root sockets, electrical wiring system malfunctions causing engine false fire warnings, failure of the aft transmission collector gear and planetary carrier retention nut, failure of the rotor blade due to undetected spar cracks, corrosion-induced cracking of main rotor blade spars, and fatigue cracks on the forward transmission rotor shaft and carrier and aft transmission planetary carrier.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Replace specific rotor shafts and extensions, inspect and modify aft transmission assemblies, inspect and replace synchronizing shaft splined adapters, inspect rotor pitch housing and blade root sockets, modify electrical wiring and test switches, inspect and modify aft transmission components, install Integral Spar Inspection System (ISIS) on rotor blades, inspect for corrosion on rotor blades, replace or modify transmission components, and ensure compliance with specified service bulletins or FAA-approved equivalents within the next 25 hours time in service after the effective date, with recurring inspections at specified intervals.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed specified hours or months as per service bulletins.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Kawasaki Heavy Industries, Limited models KV107-II and KV107-IIA helicopters certificated in all categories.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Rotor Shafts
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_78-01-17.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 78-01-17 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; KAWASAKI HEAVY INDUSTRIES, LTD Models KV-107-II and KV-107-IIA Helicopter Subject: Rotor Shafts Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 01/23/1978 Make: Kawasaki Heavy Industries, Limited Model: KV107-II | KV107-IIA 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: 78-01-17 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3122 AD NUMBER: 78-01-17 SUBJECT HEADING: Airworthiness Directives; KAWASAKI HEAVY INDUSTRIES, LTD Models KV-107-II and KV-107-IIA Helicopter ACTION: SUMMARY: DATES: Effective January 23, 1978. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 78-01-17 KAWASAKI HEAVY INDUSTRIES, LTD: Amendment 39-3122. Applies to models KV-107-II and KV-107-IIA helicopters certificated in all categories. Compliance is required as indicated. 1. To prevent fatigue cracks on the forward and aft rotor drive shafts, accomplish the following: Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, replace the forward transmission rotor shaft, P/N 107D1259, and aft rotor shaft extension, P/N 107D3147, in accordance with Kawasaki Service Bulletin No. KSB107-2 dated September 30, 1977, or an FAA-approved equivalent. Prior to the accumulation of the hours specified in KSB107-2 Section l.d., retire from service all rotor drive shafts. Compliance with Boeing-Vertol Service Bulletin No. 107-3(R-3) dated March 20, 1963, is considered an FAA-approved equivalent. 2. To prevent fatigue failure of the aft rotor transmission quill shaft, P/N 107D2067-1, accomplish the following: Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 120 hours time in service from the last inspection, remove the aft transmission assembly, inspect the mix box and aft transmission assemblies and replace parts in accordance with Kawasaki Service Bulletin No. KSB107-55 dated September 30, 1977, or an FAA-approved equivalent. Prior to installation on certificated aircraft inspect spare mix box and spare aft transmission assemblies. Compliance with Boeing-Vertol Service Bulletins No. 107-113 dated October 28, 1963, No. 107-113A dated November 22, 1963, and No. 107-182 dated October 7, 1964, is considered an FAA-approved equivalent. 3. To prevent cracking in the synchronizing shaft splined adapter, accomplish the following: Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 120 hours time in service from the last inspection, inspect synch shaft splined adapter P/N 107D3154-2 in accordance with Kawasaki Service Bulletin No. KSB107-56 (R-1) dated September 30, 1977, or an FAA- approved equivalent. Prior to the accumulation of 500 hours of operation retire from service the adapter. Adapter which is modified in accordance with KSB107-56 (R-1) may continue to remain in service for up to 2500 hours of operation. Compliance with Boeing-Vertol Service Bulletin No. 107-116(R-1) dated April 6, 1965, is considered an FAA-approved equivalent. 4. To prevent fatigue failure of the rotor pitch housing, accomplish the following: Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 25 hours time in service from the last inspection, inspect the rotor pitch housing, P/N 107R2553, and blade root sockets, P/N 42R1043, in accordance with Kawasaki Service Bulletin No. KSB107-4(R-1) dated September 30, 1977, or an FAA-approved equivalent. Prior to the accumulation of the hours stated in KSB107-4(R-1) retire from service the rotor pitch housing and blade root sockets. Compliance with Boeing-Vertol Service Bulletin No. 107-19 dated November 6, 1962, is considered an FAA-approved equivalent. 5. To prevent simultaneous engine false fire warnings caused by electrical wiring system malfunction, accomplish the following: Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, remove the engine fire detector test switch, P/N BAC-S30-AZ-3- IN5 (JANCO No. 1-1919-1N5) or P/N 1-1917-2N5, and install test switch, P/N BAC-S30AZ-3- 2N5 (JANCO No. 1-1919-2N5), and modify the wiring arrangements in accordance with Kawasaki Service Bulletin No. KSB107-137 dated September 30, 1977, or an FAA-approved equivalent. Compliance with Boeing-Vertol Service Bulletin No. 107-219 dated September 20, 1965, and No. 107-219A dated October 22, 1965, is considered an FAA-approved equivalent. 6. To prevent failure of the aft transmission collector gear and separation of the aft transmission planetary carrier retention nut either of which may cause dephasing of the main rotors, accomplish the following: Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, inspect for cracks and modify the aft transmission collector gear, P/N 107D2066-10, -12, -14, -16, and -18, in accordance with Kawasaki Service Bulletin No. KSB-V107-336, dated September 25, 1972, or an FAA-approved equivalent. Additionally, torque and install lock pins in the aft transmission planetary carrier retention nut, P/N BAC-N10GR39, P/N VS10304-39 or P/N 107D1276-7, in accordance with Kawasaki Service Bulletin KSB-V107- 332 dated January 26, 1972, or an FAA-approved equivalent. Compliance with Boeing-Vertol Service Bulletin No. A107-318(R-1) dated June 19, 1972, is considered an FAA-approved equivalent. 7. To prevent failure of the aft transmission quill shaft, P/N 107D2067, due to surface defects, accomplish the following: Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, inspect the quill shaft in accordance with Kawasaki Service Bulletin No. KSB-V107-370B dated September 30, 1977, or an FAA-approved equivalent. Compliance with Boeing-Vertol Service Bulletins No. A107-320 dated April 30, 1973, No. 107-320A dated December 21, 1973, No. A107-320B dated February 25, 1974, and No. 107-320C dated September 25, 1974, is considered an FAA-approved equivalent. 8. To prevent failure of the rotor blade, P/N 107R1202, due to undetected cracks in the spar, accomplish the following: Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, modify the rotor blades and install the Integral Spar Inspection System (ISIS) in accordance with Kawasaki SB No. KSB-V107-478 dated September 30, 1977, or an FAA-approved equivalent. Additionally, operate, inspect, and maintain the ISIS rotor blades in accordance with Kawasaki Service Bulletin No. KSB-V107-495 dated September 30, 1977, or an FAA-approved equivalent. The visual checks of the rotor blade ISIS indicator may be performed by the pilot. Compliance with Boeing-Vertol Service Bulletins No. 107-319 dated November 12, 1973, No. 107-326 dated May 20, 1974, and No. 107-329 dated June 7, 1974 is considered an FAA-approved equivalent. NOTE: Installation of the rotor blade leading edge protective strip, P/N WR1017-1, is not mandatory. 9. To prevent cracking of the main rotor blade spars due to corrosion, accomplish the following: Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 36 months, inspect for corrosion and alter, as necessary, in accordance with Kawasaki SB KSB-V107-547 dated September 30, 1977, or an FAA-approved equivalent. Compliance with Boeing-Vertol Service Bulletin No. 107-334 dated October 29, 1976, is considered an FAA-approved equivalent. 10. To prevent fatigue cracks on the forward transmission rotor shaft and carrier, and aft transmission planetary carrier, accomplish the following: Within 25 hours time in service after the effective date of this AD, unless already accomplished, replace or modify forward transmission rotor shaft and carrier, P/N AO2D1259 or P/N A07D1269, in accordance with the retirement times specified in Kawasaki SB No. KSB- V107-558 dated September 30, 1977, or an FAA-approved equivalent. Additionally, replace aft rotor transmission planetary carrier with parts of the same design, P/N 107D2419-1, prior to the accumulation of 10,000 hours of operation. Compliance with Boeing-Vertol Service Bulletin No. 107-335 dated May 15, 1977, is considered an FAA-approved equivalent. 11. The equivalent means of compliance specified in paragraphs 1 through 10 of this AD must be approved by the Chief, Engineering and Manufacturing District Office, FAA, Pacific-Asia Region, Honolulu, Hawaii. This amendment becomes effective January 23, 1978. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_78-01-17.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 78-01-17 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; KAWASAKI HEAVY INDUSTRIES, LTD Models KV-107-II and KV-107-IIA Helicopter Subject: Rotor Shafts Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 01/23/1978 Make: Kawasaki Heavy Industries, Limited Model: KV107-II | KV107-IIA 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: 78-01-17 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3122 AD NUMBER: 78-01-17 SUBJECT HEADING: Airworthiness Directives; KAWASAKI HEAVY INDUSTRIES, LTD Models KV-107-II and KV-107-IIA Helicopter ACTION: SUMMARY: DATES: Effective January 23, 1978. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 78-01-17 KAWASAKI HEAVY INDUSTRIES, LTD: Amendment 39-3122. Applies to models KV-107-II and KV-107-IIA helicopters certificated in all categories. Compliance is required as indicated. 1. To prevent fatigue cracks on the forward and aft rotor drive shafts, accomplish the following: Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, replace the forward transmission rotor shaft, P/N 107D1259, and aft rotor shaft extension, P/N 107D3147, in accordance with Kawasaki Service Bulletin No. KSB107-2 dated September 30, 1977, or an FAA-approved equivalent. Prior to the accumulation of the hours specified in KSB107-2 Section l.d., retire from service all rotor drive shafts. Compliance with Boeing-Vertol Service Bulletin No. 107-3(R-3) dated March 20, 1963, is considered an FAA-approved equivalent. 2. To prevent fatigue failure of the aft rotor transmission quill shaft, P/N 107D2067-1, accomplish the following: Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 120 hours time in service from the last inspection, remove the aft transmission assembly, inspect the mix box and aft transmission assemblies and replace parts in accordance with Kawasaki Service Bulletin No. KSB107-55 dated September 30, 1977, or an FAA-approved equivalent. Prior to installation on certificated aircraft inspect spare mix box and spare aft transmission assemblies. Compliance with Boeing-Vertol Service Bulletins No. 107-113 dated October 28, 1963, No. 107-113A dated November 22, 1963, and No. 107-182 dated October 7, 1964, is considered an FAA-approved equivalent. 3. To prevent cracking in the synchronizing shaft splined adapter, accomplish the following: Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 120 hours time in service from the last inspection, inspect synch shaft splined adapter P/N 107D3154-2 in accordance with Kawasaki Service Bulletin No. KSB107-56 (R-1) dated September 30, 1977, or an FAA- approved equivalent. Prior to the accumulation of 500 hours of operation retire from service the adapter. Adapter which is modified in accordance with KSB107-56 (R-1) may continue to remain in service for up to 2500 hours of operation. Compliance with Boeing-Vertol Service Bulletin No. 107-116(R-1) dated April 6, 1965, is considered an FAA-approved equivalent. 4. To prevent fatigue failure of the rotor pitch housing, accomplish the following: Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 25 hours time in service from the last inspection, inspect the rotor pitch housing, P/N 107R2553, and blade root sockets, P/N 42R1043, in accordance with Kawasaki Service Bulletin No. KSB107-4(R-1) dated September 30, 1977, or an FAA-approved equivalent. Prior to the accumulation of the hours stated in KSB107-4(R-1) retire from service the rotor pitch housing and blade root sockets. Compliance with Boeing-Vertol Service Bulletin No. 107-19 dated November 6, 1962, is considered an FAA-approved equivalent. 5. To prevent simultaneous engine false fire warnings caused by electrical wiring system malfunction, accomplish the following: Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, remove the engine fire detector test switch, P/N BAC-S30-AZ-3- IN5 (JANCO No. 1-1919-1N5) or P/N 1-1917-2N5, and install test switch, P/N BAC-S30AZ-3- 2N5 (JANCO No. 1-1919-2N5), and modify the wiring arrangements in accordance with Kawasaki Service Bulletin No. KSB107-137 dated September 30, 1977, or an FAA-approved equivalent. Compliance with Boeing-Vertol Service Bulletin No. 107-219 dated September 20, 1965, and No. 107-219A dated October 22, 1965, is considered an FAA-approved equivalent. 6. To prevent failure of the aft transmission collector gear and separation of the aft transmission planetary carrier retention nut either of which may cause dephasing of the main rotors, accomplish the following: Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, inspect for cracks and modify the aft transmission collector gear, P/N 107D2066-10, -12, -14, -16, and -18, in accordance with Kawasaki Service Bulletin No. KSB-V107-336, dated September 25, 1972, or an FAA-approved equivalent. Additionally, torque and install lock pins in the aft transmission planetary carrier retention nut, P/N BAC-N10GR39, P/N VS10304-39 or P/N 107D1276-7, in accordance with Kawasaki Service Bulletin KSB-V107- 332 dated January 26, 1972, or an FAA-approved equivalent. Compliance with Boeing-Vertol Service Bulletin No. A107-318(R-1) dated June 19, 1972, is considered an FAA-approved equivalent. 7. To prevent failure of the aft transmission quill shaft, P/N 107D2067, due to surface defects, accomplish the following: Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, inspect the quill shaft in accordance with Kawasaki Service Bulletin No. KSB-V107-370B dated September 30, 1977, or an FAA-approved equivalent. Compliance with Boeing-Vertol Service Bulletins No. A107-320 dated April 30, 1973, No. 107-320A dated December 21, 1973, No. A107-320B dated February 25, 1974, and No. 107-320C dated September 25, 1974, is considered an FAA-approved equivalent. 8. To prevent failure of the rotor blade, P/N 107R1202, due to undetected cracks in the spar, accomplish the following: Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, modify the rotor blades and install the Integral Spar Inspection System (ISIS) in accordance with Kawasaki SB No. KSB-V107-478 dated September 30, 1977, or an FAA-approved equivalent. Additionally, operate, inspect, and maintain the ISIS rotor blades in accordance with Kawasaki Service Bulletin No. KSB-V107-495 dated September 30, 1977, or an FAA-approved equivalent. The visual checks of the rotor blade ISIS indicator may be performed by the pilot. Compliance with Boeing-Vertol Service Bulletins No. 107-319 dated November 12, 1973, No. 107-326 dated May 20, 1974, and No. 107-329 dated June 7, 1974 is considered an FAA-approved equivalent. NOTE: Installation of the rotor blade leading edge protective strip, P/N WR1017-1, is not mandatory. 9. To prevent cracking of the main rotor blade spars due to corrosion, accomplish the following: Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 36 months, inspect for corrosion and alter, as necessary, in accordance with Kawasaki SB KSB-V107-547 dated September 30, 1977, or an FAA-approved equivalent. Compliance with Boeing-Vertol Service Bulletin No. 107-334 dated October 29, 1976, is considered an FAA-approved equivalent. 10. To prevent fatigue cracks on the forward transmission rotor shaft and carrier, and aft transmission planetary carrier, accomplish the following: Within 25 hours time in service after the effective date of this AD, unless already accomplished, replace or modify forward transmission rotor shaft and carrier, P/N AO2D1259 or P/N A07D1269, in accordance with the retirement times specified in Kawasaki SB No. KSB- V107-558 dated September 30, 1977, or an FAA-approved equivalent. Additionally, replace aft rotor transmission planetary carrier with parts of the same design, P/N 107D2419-1, prior to the accumulation of 10,000 hours of operation. Compliance with Boeing-Vertol Service Bulletin No. 107-335 dated May 15, 1977, is considered an FAA-approved equivalent. 11. The equivalent means of compliance specified in paragraphs 1 through 10 of this AD must be approved by the Chief, Engineering and Manufacturing District Office, FAA, Pacific-Asia Region, Honolulu, Hawaii. This amendment becomes effective January 23, 1978. FOOTER:
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