96-01-01 HAMILTON STANDARD: Amendment 39-9477. Docket No. 95-ANE-73. Supersedes AD 95-18-06 R1, issued August 30, 1995.
Applicability: Hamilton Standard Models 14RF-9, 14RF-19, 14RF-21; and 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15, 14SF-17, 14SF-19, and 14SF-23; and Hamilton Standard/British Aerospace 6/5500/F propellers installed on but not limited to Embraer EMB-120, EMB-120RT; Aerospatiale ATR42-100, ATR42-300, ATR42-320, ATR72, ATR72-210; de Havilland DHC-8-100 series, DHC-8-200 series, DHC-8-300 series; SAAB-SCANIA SF 340B; Canadair CL-215T, CL-415; Construcciones Aeronauticas SA (CASA) CN-235 series; and British Aerospace ATP aircraft.. NOTE: This airworthiness directive (AD) applies to each propeller identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For propellers that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (n) to request approval from the Federal Aviation Administration (FAA). This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any propeller from the applicability of this AD.
Compliance: Required as indicated, unless accomplished previously.
To prevent separation of a propeller blade due to cracks initiating in the blade taper bore, that can result in aircraft damage, and possible loss of aircraft control, accomplish the following:
(a) For Hamilton Standard Model 14RF-9 propeller blades, with Serial Numbers less than 882038 and listedin Hamilton Standard Alert Service Bulletins (ASB's) No. 14RF-9-61-A95, dated December 18, 1995, or No. 14RF-9-61-A95, Rev 1, dated December 21, 1995, installed on but not limited to Embraer EMB-120 and EMB-120RT series aircraft, accomplish the following:
(1) Within the next 150 flight cycles, after the effective date of this AD, perform an ultrasonic shear wave inspection for cracks in the blade taper bore in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14RF-9-61-A95, dated December 18, 1995, or No. 14RF-9-61-A95, Rev 1, dated December 21, 1995.
(2) For propeller blades that have been previously inspected in accordance with Hamilton Standards ASB's No. 14RF-9-61-A91, dated December 7, 1995, or No. 14RF-9-61-A91, Rev 1, dated December 15, 1995, perform an ultrasonic shear wave inspection in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14RF-9-61-A95, dated December 18, 1995, or No. 14RF-9-61-A95, Rev 1, dated December 21, 1995, within 500 flight cycles since last inspection or 150 flight cycles after the effective date of this AD, whichever occurs later.
(3) Propeller blades that cannot be inspected for cracks in accordance with Hamilton Standard ASB's No. 14RF-9-61-A95, dated December 18, 1995, or No. 14RF-9-61-A95, Rev 1, dated December 21, 1995, due to the lead wool absorbing the ultrasonic signal, must be inspected in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14RF-9-61-A91, dated December 7, 1995, or No. 14RF-9-61-A91, Rev 1 dated December 15, 1995, within the next 150 flight cycles after the effective date of this AD.
(4) Propeller blades that have ultrasonic shear wave indications that exceed the limits specified in Hamilton Standard ASB's No. 14RF-9-61-A95, dated December 18, 1995, or No. 14RF- 9-61-A95, Rev 1, dated December 21, 1995, must be inspected in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14RF-9-61-A91 dated December 7, 1995, or No. 14RF-9-61-A91, Rev 1 dated December 15, 1995.
(5) Thereafter, perform repetitive ultrasonic shear wave inspections at intervals not to exceed 500 flight cycles in accordance with the applicable SB's.
(6) Propeller blades that have ultrasonic shear wave indications that exceed the limits specified in Hamilton Standard ASB's No. 14RF-9-61-A91, dated December 7, 1995, or No. 14RF-9- 61-A91, Rev 1, dated December 15, 1995, must be removed from service, and replaced with a serviceable part prior to further flight.
(b) For Hamilton Standard Models 14SF-5, -7, -11, -15, and -23 propeller blades with Serial Numbers less than 882038 and listed in Hamilton Standard ASB's No. 14SF-61-A95, dated December 18, 1995, or No. 14SF-61-A95, Rev 1, dated December 21, 1995, installed on but not limited to Aerospatiale ATR42-100, ATR42-300, ATR42-320, ATR72 and de Havilland DHC-8-100, DHC-8-200, DHC-8-300 series aircraft, accomplish the following:
(1) Within the next 150 flight cycles, after the effective date of this AD, perform an ultrasonic shear wave inspection for cracks in the blade taper bore in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14SF-61-A95, dated December 18, 1995, or No. 14SF-61-A95, Rev 1, dated December 21, 1995.
(2) For propeller blades that have been previously inspected in accordance with Hamilton Standards ASB's No. 14SF-61-A93, dated December 7, 1995, or No. 14SF-61-A93, Rev 1, dated December 15, 1995, perform an ultrasonic shear wave inspection in accordance with the Accomplishments Instructions of Hamilton Standard ASB's No. 14SF-61-A95, dated December 18, 1995, or No. 14SF-61-A95, Rev 1, dated December 21, 1995, within 500 flight cycles since last inspection or 150 flight cycles after the effective date of this AD, whichever occurs later.
(3) Propeller blades that cannot be inspected for cracks in accordance with Hamilton Standard ASB's No. 14SF-61-A95, dated December 18, 1995, or No. 14SF-61-A95, Rev 1, dated December 21, 1995, due to the lead wool absorbing the ultrasonic signal, must be inspected in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14SF-61-A93, dated December 7, 1995, or No. 14SF-61-A93, Rev 1, dated December 15, 1995, within the next 150 flight cycles after the effective date of this AD.
(4) Propeller blades that have ultrasonic shear wave indications that exceed the limits specified in Hamilton Standard ASB's No. 14SF-61-A95, dated December 18, 1995, or No. 14SF-61- A95, dated December 21, 1995, must be inspected in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14SF-61-A93, dated December 7, 1995, or No. 14SF- 61-A93, Rev 1, dated December 15, 1995.
(5) Thereafter, perform repetitive ultrasonic shear wave inspections at intervals not to exceed 500 flight cycles in accordance with the applicable SB's.
(6) Propeller blades thathave ultrasonic shear wave indications that exceed the limits specified in Hamilton Standard ASB's No. 14SF-61-A93, dated December 7, 1995, or No. 14SF-61- A93, Rev 1, dated December 15, 1995, must be removed from service and replaced with a serviceable part prior to further flight.
(c) For Hamilton Standard Model 14RF-9 propeller blades with Serial Numbers less than 882038 and not listed in Hamilton Standard ASB's No. 14RF-9-61-A95, dated December 18, 1995, or No. 14RF-9-61-A95, Rev 1, dated December 21, 1995, installed on but not limited to Embraer EMB 120 and EMB 120RT series aircraft, accomplish the following:
(1) Within the next 300 flight cycles, after the effective date of this AD, perform an ultrasonic shear wave inspection for cracks in the blade taper bore in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14RF-9-61-A95, dated December 18, 1995, or No. 14RF-61-A95, Rev 1, dated December 21, 1995.
(2) For propeller blades that have been previously inspected in accordance with Hamilton Standards ASB's No. 14RF-9-61-A91, dated December 7, 1995, or No. 14RF-9-61-A91, Rev 1, dated December 15, 1995, perform an ultrasonic shear wave inspection in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14RF-9-61-A95, dated December 18, 1995, or No. 14RF-9-61-A95, Rev 1, dated December 21, 1995, within 300 flight cycles since last inspection or 150 flight cycles after the effective date of this AD, whichever occurs later.
(3) Propeller blades that cannot be inspected for cracks in accordance with Hamilton Standard ASB's No. 14RF-9-61-A95, dated December 18, 1995, or No. 14RF-9-61-A95, Rev. 1, dated December 21, 1995, due to the lead wool absorbing the ultrasonic signal, must be inspected in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14RF-9-61-A91, dated December 7, 1995, or No. 14RF-9-61-A91, Rev. 1, dated December 15, 1995, within the next 300 flightcycles after the effective date of this AD.
(4) Propeller blades that have ultrasonic shear wave indications that exceed the limits specified in Hamilton Standard ASB's No. 14RF-9-61-A95, dated December 18, 1995, or No. 14RF- 9-61-A95, dated December 21, 1995, must be inspected in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14RF-9-61-A91, dated December 7, 1995, or No. 14RF-9-61-A91 Rev. 1, dated December 15, 1995.
(5) Thereafter, perform repetitive ultrasonic shear wave inspections at intervals not to exceed 500 flight cycles in accordance with the applicable SB's.
(6) Propeller blades that have ultrasonic shear wave indications that exceed the limits specified in Hamilton Standard ASB's No. 14RF-9-61-A91, dated December 7, 1995, or No. 14RF-9- 61-A91, Rev. 1, dated December 15, 1995, must be removed from service and replaced with a serviceable part prior to further flight.
(d) For Hamilton Standard Models 14SF-5, -7, -11, -15,-17, -19, and -23 propeller blades with Serial Numbers less than 882038 and not listed in ASB's No. 14SF-61-A95, dated December 18, 1995, or No. 14SF-61-A95, Rev. 1, dated December 21, 1995, installed on but not limited to Aerospatiale ATR42-100, ATR42-300, ATR42-320, ATR72, ATR72-210 and de Havilland DHC-8-100, DHC-8-200, DHC-8-300 series aircraft, accomplish the following:
(1) Within the next 300 flight cycles, after the effective date of this AD, perform an ultrasonic shear wave inspection for cracks in the blade taper bore in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14SF-61-A95, dated December 18, 1995, or No. 14SF-61-A95 Rev. 1, dated December 21, 1995.
(2) For propeller blades that have been previously inspected in accordance with Hamilton Standards ASB's No. 14SF-61-A93, dated December 7, 1995, or No. 14SF-61-A93, Rev. 1, dated December 15, 1995, perform an ultrasonic shear wave inspection in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14SF-61-A95, dated December 18, 1995, or No. 14SF-61-A95, Rev. 1, dated December 21, 1995, within 500 flight cycles since last inspection or 300 flight cycles after the effective date of this AD, whichever occurs later.
(3) Propeller blades that cannot be inspected for cracks in accordance with Hamilton Standard ASB's No. 14SF-61-A95, dated December 18, 1995, or No. 14SF-61-A95, Rev. 1, dated December 21, 1995, due to the lead wool absorbing the ultrasonic signal, must be inspected in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14SF-61-A93, dated December 7, 1995, or No. 14SF-61-A93, Rev. 1, dated December 15, 1995, within the next 300 flight cycles after the effective date of this AD.
(4) Propeller blades that have ultrasonic shear wave indications that exceed the limits specified in Hamilton Standard ASB's No. 14SF-61-A95, dated December 18, 1995, or No. 14SF-61- A95, Rev. 1, dated December 21,1995, must be inspected in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14SF-61-A93, dated December 7, 1995, or No. 14SF- 61-A93, Rev. 1, dated December 15, 1995.
(5) Thereafter, perform repetitive ultrasonic shear wave inspections at intervals not to exceed 500 flight cycles in accordance with the applicable SB's.
(6) Propeller blades that have ultrasonic shear wave indications that exceed the limits specified in Hamilton Standard ASB's No. 14SF-61-A93, dated December 7, 1995, or No. 14SF-61- A93, Rev. 1, dated December 15, 1995, must be removed from service and replaced with a serviceable part prior to further flight.
(e) For all Hamilton Standard Models 14SF-17, and -19 propeller blades with Serial Numbers less than 882038, installed on but not limited to Canadair CL-215T and CL-415 series aircraft, accomplish the following:
(1) Within the next 300 flight cycles, after the effective date of this AD, perform an ultrasonic shearwave inspection for cracks in the blade taper bore in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14SF-61-A95, dated December 18, 1995, or No. 14SF-61-A95, Rev. 1, dated December 21, 1995.
(2) For propeller blades that have been previously inspected in accordance with Hamilton Standards ASB's No. 14SF-61-A93, dated December 7, 1995, or No. 14SF-61-A93, Rev. 1, dated December 15, 1995, perform an ultrasonic shear wave inspection in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14SF-61-A95, dated December 18, 1995, or No. 14SF-61-A95, Rev. 1, dated December 21, 1995, within 500 flight cycles since last inspection or 300 flight cycles after the effective date of this AD, whichever occurs later.
(3) Propeller blades that cannot be inspected for cracks in accordance with Hamilton Standard ASB's No. 14SF-61-A95, dated December 18, 1995, or No. 14SF-61-A95, Rev. 1, dated December 21, 1995, due to the lead wool absorbing the ultrasonic signal, must be inspected in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14SF-61-A93 dated December 7, 1995, or No. 14SF-61-A93, Rev. 1, dated December 15, 1995, within the next 300 flight cycles after the effective date of this AD.
(4) Propeller blades that have ultrasonic shear wave indications that exceed the limits specified in Hamilton Standard ASB's No. 14SF-61-A95, dated December 18, 1995, or No. 14SF-61- A95 Rev. 1, dated December 21, 1995, must be removed from service and inspected in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14SF-61-A93, dated December 7, 1995, or No. 14SF-61-A93 Rev. 1, dated December 15, 1995.
(5) Thereafter, perform repetitive ultrasonic shear wave inspections at intervals not to exceed 500 flight cycles in accordance with the applicable SB's.
(6) Propeller blades that have ultrasonic shear wave indications that exceed the limits specified in Hamilton Standard ASB's No. 14SF-61-A93, dated December 7, 1995, or No. 14SF-61- 93, Rev. 1, dated December 15, 1995, must be removed from service and replaced with a serviceable part prior to further flight.
(f) For all Hamilton Standard Models 14RF-19 propeller blades with Serial Numbers less than 882038, installed on but not limited to SAAB-SCANIA SF 340B series aircraft, accomplish the following:
(1) Within the next 300 flight cycles, after the effective date of this AD, perform an ultrasonic shear wave inspection for cracks in the blade taper bore in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14RF-19-61-A57, dated December 18, 1995, or No. 14RF-19-61-A57, Rev. 1, dated December 21, 1995.
(2) For propeller blades that have been previously inspected in accordance with Hamilton Standards ASB's No. 14RF-19-61-A55, dated December 7, 1995, or No. 14RF-19-61-A55, Rev. 1, dated December 15, 1995, perform an ultrasonic shear wave inspection in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14RF-19-61-A57, dated December 18, 1995, or No. 14RF-19-61-A57 Rev. 1, dated December 21, 1995, within 1,000 flight cycles since last inspection or 300 flight cycles after the effective date of this AD, whichever occurs later.
(3) Propeller blades that cannot be inspected for cracks in accordance with Hamilton Standard ASB's No. 14SF-61-A95, dated December 18, 1995, or No. 14SF-61-A95 Rev. 1, dated December 21, 1995, due to the lead wool absorbing the ultrasonic signal inspect in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14SF-61-A93, dated December 7, 1995, or No. 14SF-61-A93, Rev. 1, dated December 15, 1995, within the next 300 flight cycles after the effective date of this AD.
(4) Propeller blades that have ultrasonic shear wave indications that exceed the limits specified in Hamilton Standard ASB's 14RF-19-61-A57, dated December 18, 1995, or No. 14RF-19- 61-A57, Rev. 1, dated December 21, 1995, must be inspected in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14RF-19-61-A55, dated December 7, 1995, or No. 14RF-19-61-A55, Rev. 1, dated December 15, 1995.
(5) Thereafter, perform repetitive ultrasonic shear wave inspections at intervals not to exceed 1,000 flight cycles in accordance with the applicable SB's.
(6) Propeller blades that have ultrasonic shear wave indications that exceed the limits specified in Hamilton Standard ASB's No. 14RF-19-61-A55, dated December 7, 1995, or No. 14RF- 19-61-A55, Rev. 1, dated December 15, 1995, must be removed from service and replaced with a serviceable part prior to further flight.
(g) For all Hamilton Standard Model 14RF-21 propeller blades with Serial Numbers less than 882038, installed on but not limited to Construcciones Aeronautic SA (CASA) CN-235 series aircraft, accomplish the following:
(1) Within the next 300 flight cycles, after the effective date of this AD, perform an ultrasonic shear wave inspection for cracks in the blade taper bore in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14RF-21-61-A75, dated December 18, 1995, or No. 14RF-61-A75, Rev. 1, dated December 21, 1995.
(2) For propeller blades that have been previously inspected in accordance with Hamilton Standards ASB's No. 14RF-19-61-A55, dated December 7, 1995, or No. 14RF-19-61-A55, Rev. 1, dated December 15, 1995, perform an ultrasonic shear wave inspection in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14RF-19-61-A57, dated December 18, 1995, or No. 14RF-19-61-A57, Rev. 1, dated December 21, 1995, within 1,000 flight cycles since last inspection or 300 flight cycles after the effective date of this AD, whichever occurs later.
(3) Propeller blades that cannot be inspected for cracks in accordance with Hamilton Standard ASB's No. 14RF-21-61-A75, dated December 18, 1995,or No. 14RF-61-A75, Rev. 1, dated December 21, 1995, due to the lead wool absorbing the ultrasonic signal, must be inspected in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14RF-21-61- A73, dated December 7, 1995, or No. 14RF-21-61-A73, Rev. 1, dated December 15, 1995, within the next 300 flight cycles after the effective date of this AD.
(4) Propeller blades that have ultrasonic shear wave indications that exceed the limits specified in Hamilton Standard ASB's No. 14RF-21-61-A75, dated December 18, 1995, or No. 14RF- 21-61-A75, Rev. 1, dated December 21, 1995, must be inspected in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 14RF-21-61-A73, dated December 7, 1995, or No. 14RF-21-61-A73, Rev. 1, dated December 18, 1995.
(5) Thereafter, perform repetitive ultrasonic shear wave inspections at intervals not to exceed 2,500 flight cycles in accordance with the applicable SB's.
(6) Propeller blades that have ultrasonic shear wave indications that exceed the limits specified in Hamilton Standard ASB's No. 14RF-21-61-A73, dated December 7, 1995, or No. 14RF- 21-61-A73, Rev. 1, dated December 18, 1995, must be removed from service and replaced with a serviceable part prior to further flight.
(h) For all Hamilton Standard/British Aerospace 6/5500/F propeller blades, with Serial Numbers less than 882038, installed on but not limited to British Aerospace ATP series aircraft, accomplish the following:
(1) Within the next 300 flight cycles, after the effective date of this AD, perform an ultrasonic shear wave inspection for cracks in the blade taper bore in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 6/5500/F-61-A43, dated December 18, 1995, or No. 6/5500/F-61-A43, Rev. 1, dated December 21, 1995.
(2) For propeller blades that have been previously inspected in accordance with Hamilton Standards ASB's No. 6/5500/F-61-A41, dated December 7, 1995, or No. 6/5500/F-61- A41, Rev. 1, dated December 18, 1995, perform an ultrasonic shear wave inspection in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 6/5500/F-61-A43, or No. 6/5500/F-61-A43, Rev. 1, dated December 21, 1995, as applicable within 2,500 flight cycles since last inspection or 300 flight cycles after the effective date of this AD, whichever occurs later.
(3) Propeller blades that cannot be inspected for cracks in accordance with Hamilton Standard ASB's No. 6/5500/F-61-A43, dated December 18, 1995, or No. 6/5500/F-61-A43, Rev. 1, dated December 21, 1995, due to the lead wool absorbing the ultrasonic signal, must be inspected in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 6/5500/F-61- A41, dated December 7, 1995, or No. 6/5500/F-61-A41, Rev. 1, dated December 18, 1995, within the next 300 flight cycles after the effective date of this AD.
(4) Propeller blades that have ultrasonic shear wave indications that exceed the limits specified in Hamilton Standard ASB's No. 6/5500/F-61-A43, dated December 18, 1995, or No. 6/5500/F-61-A43, Rev. 1, dated December 21, 1995, must be inspected in accordance with the Accomplishment Instructions of Hamilton Standard ASB's No. 6/5500/F-61-A41, dated December 7, 1995, or No. 6/5500/F-61-A41 Rev. 1, dated December 18, 1995.
(5) Thereafter, perform repetitive ultrasonic shear wave inspections at intervals not to exceed 2,500 flight cycles in accordance with the applicable SB's.
(6) Propeller blades that have ultrasonic shear wave indications that exceed the limits specified in Hamilton Standard ASB's No. 6/5500/F-61-A41, dated December 7, 1995, or No. 6/5500/F-61-A41, Rev. 1, dated December 18, 1995, must be removed from service and replaced with a serviceable part prior to further flight.
(i) For all currently installed Hamilton Standard Model 14SFL11 propellers installed on Aerospatiale ATR72-210 series aircraft remove all 14SFL11 propellers from service within the next 150 flight cycles, after the effective date of this AD, and replace with serviceable Hamilton Standard 247F propellers.
(j) The ultrasonic inspection of the propeller blade taper bore must be performed by a Level II inspector who is qualified under the guidelines established by the American Society of Nondestructive Testing or MIL-STD-410 or FAA approved equivalent, and must be trained by Hamilton Standard approved personnel on how to do this inspection procedure. The individual returning the aircraft to service is required to verify that the ultrasonic inspection was accomplished in accordance with the requirements of this paragraph.
(k) For repetitive inspections, propeller blades may be evaluated to determine if the lead wool is absorbing the ultrasonic signal at any time during the 500 flight cycle repetitive inspection interval to determine if the lead wool removal is required to complete the ultrasonic shear wave inspection.
(l) For the purpose of this AD, a flight cycle is defined as one takeoff and the next landing of an aircraft. In addition, each touch and go is defined as a flight cycle, and each water load pick up for amphibian aircraft operation is defined as a flight cycle.
(m) Propeller blades removed from service after inspections performed in accordance with AD 95-18-06 R1, and subsequently inspected in accordance with the requirements of this AD and found to be serviceable, may be returned to service.
(n) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Boston Aircraft Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Boston Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with thisairworthiness directive, if any, may be obtained from the Boston Aircraft Certification Office.
(o) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished.
(p) The ultrasonic shear wave inspections and removal and replacement of propeller blades shall be done in accordance with the following Hamilton Standard Alert Service Bulletins:
DOCUMENT NO.
REVISION
DATE
No. 14RF-9-61-A91
Total Pages: 40
December 7, 1995
No. 14RF-9-61-A91
Total Pages: 42
1
December 15, 1995
No. 14RF-19-61-A55
Total Pages: 40
December 7, 1995
No. 14RF-19-61-55
Total Pages: 42
1
December 15, 1995
No. 14RF-21-61-A73
Total Pages: 40
December 7, 1995
No. 14RF-21-61-A73
Total Pages: 42
1
December 15, 1995
No. 14SF-61-A93
Total Pages: 40
December 7, 1995
No. 14SF-61-A93
Total Pages: 42
1
December 15, 1995
No. 6/5500/F-61-A41
Total Pages: 40
December 7, 1995
No. 6/5500/F-61-A41
Total Pages: 42
1
December 15, 1995
No. 14RF-9-61-A95
Total Pages: 36
December 18, 1995
No. 14RF-9-61-A95
Total Pages: 36
1
December 21, 1995
No. 14RF-19-61-A57
Total Pages: 35
December 18, 1995
No. 14RF-19-61-A57
Total Pages: 35
1
December 21,1995
No. 14RF-21-61-A75
Total Pages: 35
December 18, 1995
No. 14RF-21-61-A75
Total Pages: 35
1
December 21,1995
No. 14SF-61-A95
Total Pages: 37
December 18, 1995
No. 14SF-61-A95
Total Pages: 37
1
December 21, 1995
No. 6/5500/F-61-A43
Total Pages: 35
December 18, 1995
No. 6/5500/F-61-A43
Total Pages: 35
1
December 21, 1995
This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Hamilton Standard, One Hamilton Road, Windsor Locks, CT 06096-1010; telephone (203) 654-6876. This information may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(q) This amendment supersedes priority letter AD 95-18-06 R1, issued August 30, 1995. Note: AD 95-18-06 R1 revised priority letter 95-18-06, which superseded telegraphic AD T95-18-51 and AD 95-05-03. Also, AD 95-05-03 superseded 94-09-06.
(r) This amendment becomes effective on January 19, 1996.