AD 96-09-03

This amendment adopts a new airworthiness directive (AD), applicable to Societe Nationale Industrielle Aerospatiale and Eurocopter France Model SA-365N, N1, and N2 helicopters, that requires an inspection of the door jettison systems to determine if the handle shafts are locked to the jettison systems. If the inspection indicates the handle shafts are locked to the jettison systems, this AD requires installation of a snapwire on the jettison systems and a visual inspection of the door jettison handles to determine whether two spring pins are installed, and installation of a second spring pin, if necessary. If the initial inspection indicates that the handle shafts are not locked to the jettison systems, this AD requires replacement of the sheared spring pin with two spring pins. This amendment is prompted by a factory inspection performed by the manufacturer that revealed that the forward passenger door jettison handles may have been fitted with one spring pin instead of two spring pins at the door jettison handle attachment points. The actions specified by this AD are intended to prevent a loss of the doors in flight and subsequent damage to the horizontal stabilizer, main fin, or lateral fins.

Final rule

96-09-03 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE AND EUROCOPTER FRANCE (EUROCOPTER FRANCE): Amendment 39-9577. Docket No. 95-SW-01-AD.

Applicability: Model SA-365N, N1, and N2 helicopters, serial numbers (S/N) 6008, 6033, 6083, 6084, 6085, 6093, 6120 and higher that have not been modified in accordance with Avis De Modification (AMS) 365A07-56B15, 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 (b) 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 a loss of the doors in flight and subsequent damage to the horizontal stabilizer, main fin, or lateral fins, accomplish the following:

(a) Within 30 days after the effective date of this AD, for both the left and right forward passenger door jettison systems, cut the snapwire on the door jettison handle, and, without turning the handle completely, determine whether the handle is locked to the jettison mechanism.

(1) If the door jettison handle shaft is locked to the jettison system,

(i) Install the snapwire, part number (P/N) L23321, or annealed copper safety wire, black enameled, 0.3mm diameter, on each door jettison handle.

(ii) Within 500 hours time-in-service (TIS) after the effective date of this AD, accomplish the following in accordance with the applicable maintenance manual:

(A) Remove the doors and remove the trimming panels from the passenger door posts. Visually inspect each door to determine whether two spring pins are installed to fasten each jettison handle.
(B) If only one spring pin is installed, install a second spring pin.
(C) Reinstall the trimming panel.
(D) Reinstall the door.
(E) Install the snapwire as specified in paragraph (a)(1)(i) of this AD.

(2) If a door jettison handle shaft is not locked to the jettison system, before further flight, accomplish the following.

(i) Remove the door and the trimming panel.
(ii) Remove the sheared spring pin.
(iii) Replace the sheared spring pin with two spring pins.
(iv) Reinstall the door trimming panels.
(v) Reinstall the door.(vi) Install the snapwire as described in paragraph (a)(1)(i) of this AD.

NOTE 2: Eurocopter Service Bulletin SA 365, No. 01.38, dated January 31, 1994, pertains to this AD.

(b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used when approved by the Manager, Rotorcraft Standards Staff, FAA, Rotorcraft Directorate. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Standards Staff.

NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff.

(c) 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 to a location where the requirements of this AD can be accomplished.

(d) This amendment becomes effective on May 30, 1996.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to Societe Nationale Industrielle Aerospatiale and Eurocopter France Model SA-365N, N1, and N2 helicopters was published in the Federal Register on November 2, 1995 (60 FR 55681). That action proposed to require, within 30 days after the effective date of the AD, an inspection of the door jettison systems to determine if the handle shafts were locked to the jettison systems. If the inspection indicated the handle shafts were locked to the jettison systems, that action proposed to require installation of a snapwire on the jettison systems and within 500 hours time-in-service, a visual inspection of the door jettison handles to determine whether two spring pins were installed, and installation of a second spring pin, if necessary. If the initial inspection indicated that the handle shafts were not locked to the jettison systems, the action proposed to require, before further flight, replacement of the sheared spring pin with two spring pins.

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposal or the FAA's determination of the cost to the public. The FAA has determined that air safety and the public interest require the adoption of the rule as proposed, except for various non-substantive editorial changes and deleting the incorporation by reference of the service bulletin. The FAA has determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD.

The FAA estimates that 27 helicopters of U.S. registry will be affected by this AD, that it will take approximately 8 work hours per helicopter to accomplish the actions, and that the average labor rate is $60 per work hour. Required parts will cost approximately $230 per helicopter. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $19,170.

The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.

For the reasons discussed above, I certify that this action (1) is not a " significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES."

List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39 - AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 USC 106(g), 40113, 44701.

39.13 - [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: