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95-18-06 PL: 95-18-06 Hamilton Standard: Priority Letter issued on August 28, 1995. Docket No. 95-ANE-50. Supersedes Telegraphic AD T95-18-51 and AD 95-05-03, Amendment 39-9170. 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 and EMB 120-RT; SAAB-SCANIA SF 340B; Aerospatiale ATR42-100, ATR42-300, ATR42-320, ATR72; DeHavilland DHC-8-100 series, DHC-8-300 Series; Construcciones Aeronauticas SA (CASA) CN-235 series and CN-235-100; Canadair CL-215T and CL-415; and British Aerospace ATP airplanes. NOTE: This 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 ofthe requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (h) 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, installed on Embraer EMB-120 series aircraft, within the next 10 flight cycles after the effective date of this AD, remove from service propeller blades that have been ultrasonically shear wave inspected in accordance with AD 94-09-06 or AD 95-05-03, removed from service due to crack indications, and subsequently reworked and returned to service. These propeller blades include, but are not limited to, the following serial numbers: 847598 855196 851646 855859 852085 857375 852561 858696 853151 859824 854530 860589 854535 867590 854838 876707 855014 880245 855042 (b) For Hamilton Standard Models 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 propeller blades, installed on aircraft other than Embraer EMB-120 series aircraft, within the next 10 flight cycles after the effective date of this AD, unless inspected previously in accordance with Telegraphic AD T95-18-51, perform an ultrasonic shear wave inspection for cracks in the blade taper bore of propeller blades that have been ultrasonically inspected in accordance with AD 94-09-06 or AD 95-05-03, removed from service due to crack indications, and subsequently reworked and returned to service. Thereafter, at intervals not to exceed 1,250 flight cycles since last inspection, perform an ultrasonic shear wave inspection for cracks in the blade taper bore of propeller blades. Perform the ultrasonic shear wave inspection in accordance with the Accomplishment Instructions of the following Hamilton Standard Alert Service Bulletins (ASB's), as applicable: No. 14RF-21-61-A68, No. 14SF-61-A88, No. 14RF-19-61-A49, No. 6/5500/F-61-A36; all dated August 25, 1995. Remove cracked propeller blades from service and replace with serviceable parts. (c) For Hamilton Standard Model 14RF-9 propeller blades, installed on Embraer EMB-120 series aircraft, not affected by paragraph (a) of this AD, perform ultrasonic shear wave inspections in accordance with theAccomplishment Instructions of Hamilton Standard ASB No. 14RF-9-61- A85, dated August 28, 1995. Remove cracked propeller blades from service and replace with serviceable parts: (1) For propeller blades with 1,250 or more flight cycles since last ultrasonic shear wave inspection on the effective date of this AD, or that have not been ultrasonically shear wave inspected, perform an ultrasonic shear wave inspection for cracks within the next 50 flight cycles after the effective date of this AD. (2) For propeller blades with less than 1,250 flight cycles since last ultrasonic shear wave inspection on the effective date of this AD, perform an ultrasonic shear wave inspection for cracks within the next 50 flight cycles after the effective date of this AD, or prior to accumulating 1,250 flight cycles, whichever occurs later. (3) Thereafter, perform repetitive ultrasonic shear wave inspections at intervals not to exceed 1,250 flight cycles since last inspection. (d) For Hamilton Standard Models 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 propeller blades; identified by serial number in the ASB's listed in this paragraph, installed on aircraft other than Embraer EMB-120 aircraft, and not affected by paragraph (b) of this AD, perform ultrasonic shear wave inspections in accordance with the Accomplishment Instructions of Hamilton Standard ASB's, as applicable: No. 14RF-21-61-A69, No. 14SF-61-A89, No. 14RF-19- 61-A50, No. 6/5500/F-61-A37; all dated August 28, 1995. Remove cracked propeller blades from service and replace with serviceable parts: (1) For propeller blades with 1,250 or more flight cycles on the effective date of this AD, or that have not been ultrasonically shear wave inspected, perform an ultrasonic shear wave inspection for cracks within the next 150 flight cycles after the effective date of this AD. (2) For propeller bladeswith less than 1,250 flight cycles on the effective date of this AD, perform an ultrasonic shear wave inspection for cracks within the next 150 flight cycles after the effective date of this AD, or prior to accumulating 1,250 flight cycles, whichever occurs later. (3) Thereafter, perform repetitive ultrasonic shear wave inspections at intervals not to exceed 1,250 flight cycles since last inspection. (e) No ultrasonic shear wave inspections are required for Hamilton Standard Models 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 propeller blades, that have been shotpeened in the taper bore during manufacture, and not identified by serial numbers in the ASB's listed in paragraph (b) of this AD. (f) Propeller blades removed from service in accordance with this AD may not be returned to service. (g) For the purpose of this AD, a flight cycle is defined as one takeoff andthe next landing of an aircraft. (h) 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 this airworthiness directive, if any, may be obtained from the Boston Aircraft Certification Office. (i) 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. (j) Copies of the applicable service information may be obtained from Hamilton Standard, One Hamilton Road, Windsor Locks, CT 06096-1010; telephone (203) 654-6876. This information may be examined at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA. (k) Priority Letter AD 95-18-06, issued August 28, 1995, becomes effective upon receipt. (l) Priority Letter AD 95-18-06 supersedes Telegraphic AD T95-18-51 and AD 95-05-03, Amendment 39-8854.
85-15-06: 85-15-06 SIKORSKY AIRCRAFT: Amendment 39-5164. Applies to Sikorsky Model S-76A helicopters certificated in all categories. Compliance is required prior to further flight, unless already accomplished. To prevent failure of certain tail rotor drive shaft bearings which may have been installed without lubricant, accomplish the following in accordance with Sikorsky Aircraft Alert Service Bulletin (ASB) 76-66-20, paragraph E.1, dated July 25, 1985. (a) Remove all Part Number (P/N) SB1138-101 bearings manufactured by MRC not identified with either a white dot on the grease fitting or a serial number and with under 100 hours operating time. (b) Replace removed bearings with MRC P/N SB1138-101 bearings identified with either a white dot on the grease fitting or a serial number or both, or with the alternate bearing manufactured by Fafnir and approved for this installation. (c) Aircraft may be ferried in accordance with the provisions of FAR Section 21.197 and 21.199 to a base where the AD can be accomplished. (d) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Boston Aircraft Certification Office, ANE150, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Boston Aircraft Certification Office, ANE-150, may adjust the compliance time specified in this AD. Sikorsky Aircraft ASB 76-66-20 is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Mr. R. E. Warren, Sikorsky Aircraft Division, United Technologies Corporation, North Main Street, Stratford, Connecticut 06601. These documents also may be examined at the Rules Docket, Office of the Regional Counsel, FAA, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas 76106. This amendment becomes effective November 25, 1985, as to all persons except those persons to whom it was made immediately effective by priority letter AD No. 85-15-06, issued July 30, 1985, which contained this amendment.
98-16-05: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300-600 series airplanes, that requires inspections of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door to detect cracks and corrosion, and repair, if necessary. This amendment also requires inspections to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the door structures; and repair, if necessary. In addition, this amendment provides for optional terminating action for certain inspections. This amendment is prompted by reports indicating that corrosion was found behind the scuff plates at exit and cargo doors, and fatigue cracks originated from certain fastener holes located in adjacent structure. The actions specified by this AD are intended to detect and correct such corrosion and fatigue cracking, which could result in reduced structural integrity of the door surroundings.
2019-09-04: We are adopting a new airworthiness directive (AD) for certain Leonardo S.p.A. (Type Certificate previously held by Finmeccanica S.p.A., AgustaWestland S.p.A.) Model AW109SP helicopters. This AD requires inspecting and altering the rescue hoist. This AD was prompted by a report of a damaged hoist cable that detached after load application. The actions of this AD are intended to address an unsafe condition on these products.
84-19-07: 84-19-07 BRITISH AEROSPACE VISCOUNT: Amendment 39-4918. Applies to Model 700 and 800 series airplanes, certificated in all categories, as indicated in each paragraph below. To prevent failure of certain components in the hydraulic system, entry and cargo doors, or rudder mechanism, accomplish the following within the compliance time specified in each paragraph below, unless previously accomplished: A. For all Model 700 series pre-Modification D.2883 and for all Model 800 series pre-Modification FG.1553 which are equipped with hydraulic system Micronic Filters, Part Numbers A6301, A6302, or A5641, inspect and replace hydraulic filter attachment bolts in accordance with Preliminary Technical Leaflet (PTL) No. 308 for all Model 700 series and PLT No. 177 for all 800 series airplanes, both dated February 7, 1979, within 1000 hours time in service after the effective date of this AD. B. Inspect and modify entrance and cargo doors of Model 700 series airplanes in accordancewith PTL No. 235, Issue 3, dated December 8, 1968, within 350 hours time in service after the effective date of this AD. Subsequent inspections, as denoted in paragraph 4.2 of the PTL, must be accomplished at intervals not to exceed 350 hours from the previous inspection. Modify Model 700 series airplanes in accordance with the instructions in BAe bulletin for Modification No. D.3051, Issue 1, dated April 23, 1962, and Issue 2, dated May 17, 1978, within 350 hours time in service after the effective date of this AD, for all entrance and cargo door bolt sleeves. C. Replace rudder spigot and mounting block on Model 700 series and Model 800 series airplanes in accordance with PTL No. 311, Issue 1, and PTL No. 180, Issue 1, respectively, both dated May 22, 1981, at or before 29,500 hours total time in service or within the next 500 hours after the effective date of this AD, whichever occurs later. D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and modifications required by this AD. This amendment becomes effective October 22, 1984.
99-26-17: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes, that requires modification of the engine intake ducts to provide new cable routes and improved contamination protection of connectors on the engine intake de-icing system. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent chafing and subsequent damage to the engine intake de-icing system wiring, and contamination of electrical connectors and plugs. Damage to system wiring or contamination of the electrical connectors or plugs could result in loss of engine intake de-icing capability, accretion of ice in the intake duct, ice ingestion, and consequent engine flameout.
99-27-07: This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A300 B4-600R and A300 F4-600R series airplanes, that currently requires a one-time visual inspection for damage of the center tank fuel pumps and fuel pump canisters, and replacement of damaged fuel pumps and fuel pump canisters with new or serviceable parts. This amendment also requires repetitive visual inspections of the fuel pumps and repetitive eddy current inspections of the fuel pump canisters, and replacement of damaged fuel pumps and fuel pump canisters with new or serviceable parts. This amendment also reduces the applicability to include only those airplanes that have a trim tank system installed. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect damage to the fuel pump and fuel pump canister, which could result in loss of flame trap capability and could provide a fuel ignition source in the center fuel tank.
2019-08-13: We are adopting a new airworthiness directive (AD) for certain Textron Aviation, Inc. (type certificate previously held by Cessna Aircraft Company) Models 525, 525A, and 525B airplanes with Tamarack active load alleviation system (ATLAS) winglets installed in accordance with Supplemental Type Certificate (STC) SA03842NY. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as malfunction of the ATLAS. We are issuing this AD to require actions to address the unsafe condition on these products.
84-25-04: 84-25-04 BOEING: Amendment 39-4968. Applies to all Boeing Model 747 airplanes equipped with Landing Rollout Control Unit automatic landing systems, Boeing P/N 60B00013-757 or 60B00013-759. \n\n\tTo prevent a hazardous condition due to loss of the autopilot battery power, within 30 days after the effective date of this AD install a placard on the autopilot P10 mode select panel which reads as follows: "DO NOT USE THE LAND MODE," unless already accomplished. The placard may be removed when the airplane wiring has been modified in accordance with Boeing Service Bulletin 747-22A2152, dated November 16, 1984, or later FAA approved revision; or any alternate means of compliance which provides an equivalent level of safety approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tAll persons affected by this proposal who have not already received the Service Bulletin may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box3707, Seattle, Washington 98168. These documents may also be examined at the FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective January 2, 1985.
99-19-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model Dornier 328-100 series airplanes, that requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This amendment is prompted by reports of inflight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to ensure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.