AD 98-07-03 SUPERSEDED

This document corrects a technical bulletin date in airworthiness directive (AD) 98-07-03 that was incorrectly published in the Federal Register on March 24, 1998 (63 FR 14026). This AD is applicable to Bell Helicopter Textron, Inc. Model 412 helicopters and Agusta S.p.A Model AB 412 helicopters and requires a temporary reduction of the never-exceed velocity (Vne) limitation until an inspection of the tail rotor yoke (yoke) assembly for fatigue damage and installation of a redesigned yoke flapping stop are accomplished. Recurring periodic and special inspections to detect occurrences of yoke overload are also required.

Final rule; correction

98-07-03 BELL HELICOPTER TEXTRON, INC. and AGUSTA S.p.A.: Amendment 39-10421. Docket No. 97-SW-58-AD.

Applicability: Bell Helicopter Textron, Inc. Model 412 helicopters, serial numbers (S/N) 33001 through 33213, 34001 through 34024, 36001 through 36121, 46400 through 46434, 46437, and Agusta S.p.A. Model AB412 helicopters, S/N prior to and including S/N 25806, and S/N 25901; certificated in any category.

NOTE 1: This AD applies to each helicopter 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 helicopters 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 (e) to request approval from the 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 helicopter from the applicability of this AD.

Compliance: Required as indicated, unless accomplished previously.

To prevent fatigue failure of the tail rotor yoke (yoke), that could result in loss of control of the helicopter, accomplish the following:

(a) Before further flight, review the historical records of the yoke assembly, part number (P/N) 212-011-702-all dash numbers, for any static or dynamic incident history, other than normal usage, that could have imposed a bending load on the yoke, but did not require yoke assembly replacement; for example, an incident in which a damaged tail rotor blade was replaced due to a blade strike. If such a history exists, replace the yoke with an airworthy yoke.

(b) Before further flight, unless paragraph (c) of this AD has been accomplished previously:

(1) Install a Never Exceed Velocity (Vne) red line at 120 knots indicated airspeed (KIAS) on the pilot and copilot airspeed indicators using red tape or paint, and a slippage indicator on the instrument case and glass.

(2) Install a placard made of material that is not easily erased, disfigured, or obscured on the instrument panel in clear view of the pilot and copilot:

"Observe temporary Maximum Never Exceed (Vne) airspeed red line (marked at 120 knots indicated airspeed (KIAS). Vne is 20 KIAS less than the value presented on the airspeed limitation placard for each ambient condition."

(3) Insert the applicable Bell Helicopter Textron 412 Temporary Revision, dated August 16, 1996, into the Model 412 Rotorcraft Flight Manual (RFM),or Agusta AB412EP Temporary Revision No. 2 into the Model AB412 RFM.

(c) Within 180 calendar days:

(1) Remove yoke assembly, P/N 212-011-702-all dash numbers, and replace it with an airworthy yoke assembly, P/N 212-011-702-all dash numbers, with zero hours time-in-service (TIS), or an airworthy yoke (regardless of TIS) that has passed a one-time x-ray diffraction inspection in accordance with Bell Helicopter Textron ASB 412-96-89, Revision A, dated October 17, 1997; Bell Helicopter Textron ASB 412CF-96-01, dated September 3, 1996; or, Agusta Bolletino Tecnico (Technical Bulletin) No. 412-65, dated April 17, 1997, whichever is applicable.

(2) Install an airworthy tail rotor flapping stop, P/N 212-011-713-103.

(3) If requirements are accomplished in accordance with paragraphs (c)(1) and (c)(2) of this AD, remove the 120 KIAS redline from the pilot and copilot airspeed indicators;remove the Vne airspeed restriction placard; and remove the Bell Helicopter Textron 412 Temporary Revision, dated August 16, 1996, or Agusta AB Temporary Revision No. 2, as applicable, from the RFM.

(d) After accomplishing paragraph (c) of this AD, thereafter inspect the yoke assembly and tail rotor flapping stop at intervals not to exceed 25 hours TIS in accordance with Part III, Recurring 25-Hour Special Inspection and Conditional Inspection Requirement, of Bell Helicopter Textron ASB 412-96-89, Revision A, dated October 17, 1996; Bell Helicopter Textron ASB 412CF-96-01, dated September 3, 1996; or Agusta Bolletino Tecnico (Technical Bulletin) No. 412-65, dated April 17, 1997, as applicable.

(e) 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, Rotorcraft Standards Staff, Rotorcraft Directorate, FAA. Operators shall submit their requeststhrough an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Standards Staff.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff.

(f) 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 helicopter at airspeeds not to exceed 120 KIAS to a location where the requirements of this AD can be accomplished.

(g) The inspections and installations shall be done in accordance with Bell ASB 412-96-89, Revision A, dated October 17, 1997; Bell Helicopter Textron ASB 412CF-96-01, dated September 3, 1996; or Agusta Technical Bulletin No. 412-65, dated April 17, 1997. 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 Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101, telephone (817) 280-3391, fax (817) 280-6466; or Agusta, 21017 Cascina Costa di Samarate (VA), Via Giovanni Agusta 520, telephone (0331) 229111, fax (0331) 229605-222595. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

NOTE 3: The subject of this AD is addressed in Registro Aeronautico Italiano (Italy) AD 97-223, dated January 8, 1997.

(h) This amendment becomes effective on April 8, 1998.

Airworthiness Directive (AD) 98-07-03, amendment 39-10421, applicable to Bell Helicopter, Textron, Inc. Model 412 Helicopters and Agusta S.p.A Model AB 412 helicopters was published in the Federal Register on March 24, 1998 (63 FR 14026). That AD requires a temporary reduction of the Vne limitation until an inspection of the yoke assembly for fatigue damage and installation of a redesigned yoke flapping stop are accomplished. Recurring periodic and special inspections to detect occurrences of yoke overload are also required.

As published, the Agusta Technical Bulletin date given in the Supplementary Information and in paragraphs (c)(1) and (g) is incorrect.

Since no other part of the regulatory information has been changed, the final rule is not being republished.

The effective date of the AD remains April 8, 1998.

In rule FR Doc. 98-7414 published on March 24, 1998 (63 FR 14026), make the following corrections:
39.13 [Corrected]
(1) On page 14027, in the first column under Supplementary Information, change "December 2, 1996" to "April 17, 1997."
(2) On page 14028, in paragraphs (c)(1), (d), and (g), change "December 2, 1996" to "April 17, 1997."
Issued in Fort Worth, Texas, on July 10, 1998.

Mr. Shep Blackman, Aerospace Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5296, fax (817) 222-5961.