# AD 2002-17-52: Tail rotor blade - Type: Emergency airworthiness directive - Status: Historical - Products: Agusta A119 - Issued: August 21, 2002 - Issued as: Emergency AD - Superseded by: [AD 2002-21-04](https://openairdocs.org/ad/2002-21-04) - Product type: Aircraft, Rotorcraft - Docket: 2002-SW-43-AD - Registered aircraft: 12 may be affected, by airframe or engine model (OpenAirDocs) - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/076CCA1FA597CD8486256C1C00774EF0.0001 - DRS record last changed: August 7, 2025 - Page: https://openairdocs.org/ad/2002-17-52 ## The airworthiness directive 1 EMERGENCY AIRWORTHINESS DIRECTIVE Aircraft Certification Service Washington, DC U.S. Department of Transportation Federal Aviation Administration We post Emergency ADs on the internet at "av-info.faa.gov" DATE: August 21, 2002 AD #: 2002-17-52 Send to all U.S. owners and operators of Agusta S.p.A. Model A119 helicopters. This superseding Emergency Airworthiness Directive (AD) is prompted by a failure of a tail rotor blade that resulted in a forced auto-rotative landing. The failure of the tail rotor blade was due to a fatigue crack. This condition, if not detected, could result in the failure of a tail rotor blade and subsequent loss of control of the helicopter. The FAA has reviewed Agusta Alert Bollettino Tecnico No. 119-6, Revision A, dated July 12, 2002 (BT), which describes procedures for checking and inspecting both sides of the tail rotor blades, part number (P/N) 109-8132-01-111, for a crack, reducing the helicopter never exceed speed (Vne), modifying the tail rotor, hub and blades assembly, and establishing a retirement life for the tail rotor control rod. On July 9, 2002, the FAA issued Emergency AD 2002-14-51, which applies to Agusta Model A109E and A119 helicopters. That AD requires, before each flight, visually checking each tail rotor blade on both sides for a crack. That AD also requires, within 5 hours time-in-service (TIS) and thereafter at intervals not to exceed 5 hours TIS, inspecting each tail rotor blade for a crack with a 5x or higher magnifying glass. If you are unable to determine by the visual inspection whether there is a crack, the AD requires conducting a dye penetrant inspection. Replacing any cracked tail rotor blade with an airworthy blade is also required before further flight. That AD was prompted by the failure of a tail rotor blade resulting in a forced auto-rotative landing. The failure of the tail rotor blade was due to a fatigue crack. Since the issuance of AD 2002-14-51, the manufacturer determined, and we agree, that reducing the Vne is necessary to reduce the tail rotor loading. Further, we have determined that additional tail rotor hub and blades assembly modifications are necessary for the Agusta Model A119 helicopters that are not required for the Model A109E helicopters, so we are superseding AD 2002-14-51 and issuing a separate AD for each model. The reduction in Vne and the additional modifications support the increase in the visual inspection interval from 5 hours TIS to 25 hours TIS. The Ente Nazionale per l’ Aviazione Civile (ENAC), the airworthiness authority for Italy, notified the FAA that an unsafe condition may exist on these helicopter models. The ENAC advises of the failure of a tail rotor blade that resulted in a forced auto-rotative landing. The ENAC classified the BT as mandatory and issued AD No. 2002-367, dated July 16, 2002, to ensure the continued airworthiness of these helicopters. This helicopter model is manufactured in Italy and is type certificated for operation in the United States under the provisions of 14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the applicable bilateral agreement, the ENAC has kept the FAA informed of the situation described above. The FAA has examined the findings of the ENAC, reviewed all available information, and determined 2 that AD action is necessary for products of this type design that are certificated for operation in the United States. The unsafe condition described previously is likely to exist or develop on other helicopters of the same type design. Therefore, this AD requires: • Installing a placard in the helicopter and marking the airspeed indication at 132 knots indicated airspeed (KIAS) before further flight; • Visually checking the tail rotor blades on both sides for a crack before each start of the helicopter engine; • Visually inspecting the tail rotor blades with a 5x or higher magnifying glass within 25 hours TIS and thereafter at intervals not to exceed 25 hours TIS, and anytime an increase in vibration occurs, and conducting a dye-penetrant inspection if you are unable to determine by the visual inspection whether or not there is a crack; • Replacing any cracked tail rotor blade with an airworthy blade before further flight; • Modifying the tail rotor hub and blades assembly with a new grip and bushings assembly, reidentifying the tail rotor hub and grips assembly, and reidentifying the tail rotor hub and blades assembly, which is terminating action for the Vne reduction indicated by the airspeed marking and the Vne placard and restores the original Vne; and • Establishing a retirement life for the tail rotor control rod. The actions must be accomplished in accordance with the BT described previously. An owner/operator (pilot) may perform the visual check required by paragraph (b) of this AD and must enter compliance with that paragraph into the helicopter maintenance records in accordance with 14 CFR 43.11 and 91.417(a)(2)(v). A pilot may perform this check because it involves only a visual check for a crack in the tail rotor blade and can be performed equally well by a pilot or a mechanic. This rule is issued under 49 U.S.C. Section 44701 pursuant to the authority delegated to me by the Administrator, and is effective immediately upon receipt of this emergency AD. 2002-17-52 AGUSTA S.p.A.: Docket No. 2002-SW-43-AD. Supersedes Emergency AD 2002-14-51, Docket No. 2002-SW-35-AD. Applicability: Model A119 helicopters, with hub and tail rotor blades assembly, part number (P/N) 109-8131-02-149, or tail rotor blades, P/N 109-8132-01-111, installed, certificated in any category. Note 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (i) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the tail rotor blade and subsequent loss of control of the helicopter, accomplish the following: 3 (a) Before further flight, install a placard in the helicopter and mark the airspeed indicator at 132 knots indicated airspeed (KIAS) to indicate a reduction in the helicopter never exceed speed (Vne) by 30 KIAS. Make and install the placard in accordance with the Compliance Instructions, Part I, of Agusta Alert Bollettino Tecnico No. 119-6, Revision A, dated July 12, 2002 (BT). On the glass of the airspeed indicator, apply a red mark over the value of 132 KIAS. (b) Before each start of the helicopter engine, visually check both sides of each tail rotor blade for a crack in the area depicted in Figure 1 of this AD. An owner/operator (pilot) holding at least a private pilot certificate may perform this visual check and must enter compliance with this paragraph into the aircraft maintenance records in accordance with 14 CFR 43.11 and 91.417(a)(2)(v). See Figure 1: Note 2: Paint irregularities on the tail rotor blade may be due to a crack. (c) Within 25 hours time-in-service (TIS), and thereafter at intervals not to exceed 25 hours TIS, and any time an increase in vibration levels occur, using a 5x or higher magnifying glass, visually inspect each tail rotor blade for a crack in accordance with the Compliance Instructions, Part III, paragraphs 1. through 5., of the BT. Reporting to Agusta Service Engineering is not required. If you are unable to determine by the visual inspection whether there is a crack, dye penetrant inspect the tail rotor blade for a crack in accordance with the Compliance Instructions, Part III, paragraph 6., of the BT. (d) Replace any cracked tail rotor blade with an airworthy blade before further flight. (e) Not later than October 30, 2002, in accordance with the Compliance Instructions, Part IV, and Figure 2 of the BT: (1) Install a new grip and bushing assembly, P/N 109-8131-02-147, into tail rotor hub and blade assembly, P/N 109-8131-02-149; 4 (2) Reidentify the modified tail rotor hub and grips assembly, P/N 109-8131-02-141, as P/N 109- 8132-01-153; and (3) Reidentify the modified tail rotor hub and blade assembly, P/N 109-8131-02-149, as P/N 109- 8131-02-155. Returning the grips to the manufacturer is not required by this AD. (f) After completing the actions required by paragraph (e) of this AD, remove the Vne placard and the airspeed indicator marking at 132 KIAS that were installed in accordance with paragraph (a) of this AD. Modifying and reidentifying the parts as required by paragraph (e) of this AD is terminating actions for the requirements of paragraph (a) of this AD and restores the original Vne. (g) After completing the actions required by paragraph (e) of this AD, establish a retirement life of 1,000 hours TIS for tail rotor control rod, P/N 109-0135-02-101. (h) After completing the actions required by paragraph (e) of this AD, revise the helicopter Airworthiness Limitations Section of the Agusta Model A119 helicopter maintenance manual by inserting a 1,000 hour TIS retirement life for each tail rotor control rod, P/N 109-0135-02-101. (i) 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, Regulations Group, Rotorcraft Directorate, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Regulations Group. Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Regulations Group. (j) Special flight permits will not be issued. (k) Copies of the applicable service information may be obtained from Agusta, 21017 Cascina Costa di Samarate (VA) Italy, Via Giovanni Agusta 520, telephone 39 (0331) 229111, fax 39 (0331) 229605-222595. (l) Emergency AD 2002-17-52, issued August 21, 2002, becomes effective upon receipt. Note 4: The subject of this AD is addressed in Ente Nazionale per l’Aviazione Civile (Italy) AD No. 2002-367, dated July 16, 2002. FOR FURTHER INFORMATION CONTACT: Richard Monschke, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, Texas 76193-0110, telephone (817) 222- 5116, fax (817) 222-5961. Issued in Fort Worth, Texas, on August 21, 2002. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. ## Affected data sheets (1) (OpenAirDocs) The type certificate data sheets whose models the AD names. - [TCDS H7EU](https://openairdocs.org/tcds/H7EU): Leonardo S.p.A.; names 1 of 10 models: A119 ## Registered aircraft it may apply to (OpenAirDocs) Matched by airframe and engine model; the AD's applicability may narrow it by serial number, part number or equipment. - Aircraft: 12 (12 by airframe model, 0 by engine model) - Makers: Agusta 12 Models with the most aircraft: - [Agusta A119](https://openairdocs.org/model/agusta-a119): 12 aircraft (airframe model) All 1 models: https://openairdocs.org/ad/2002-17-52/models.md Every aircraft: https://openairdocs.org/ad/2002-17-52/aircraft.md ## Related documents - [AD 2002-21-04](https://openairdocs.org/ad/2002-21-04): Tail rotor blade · Agusta A119. Effective Oct 31, 2002. Supersedes this AD Its text cites no advisory circulars or STCs. --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.