[Federal Register Volume 60, Number 212 (Thursday, November 2, 1995)]
[Proposed Rules]
[Pages 55681-55683]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-27203]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-SW-01-AD]


Airworthiness Directives; Societe Nationale Industrielle 
Aerospatiale and Eurocopter France Model SA-365N, N1, and N2 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to Societe Nationale Industrielle 
Aerospatiale and Eurocopter France (Eurocopter France) Model SA-365N, 
N1, and N2 helicopters. This proposal would require an inspection of 
the door jettison systems to detemine if the handle shafts are locked 
to the jettison systems. If the inspection indicates the handle shafts 
are locked to the jettison systems, the proposal would require 
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, the proposal would require 
replacement of the sheared spring pin with two spring pins. This 
proposal 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 the proposed AD are intended to prevent a loss of the 
doors in flight and subsequent damage to the horizontal stabilizer, 
main fin, or lateral fins.

DATES: Comments must be received by January 2, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Assistant Chief Counsel, Attention: 
Rules Docket No. 95-SW-01-AD, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas 76137. Comments may be inspected at this location between 9:00 
a.m. and 3:00 p.m., Monday through Friday, except Federal holidays.
    The service information referenced in the proposed rule may be 
obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand 
Prairie, Texas 75053-4005. This information may be examined at the FAA, 
Office of the Assistant Chief Counsel, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas.


[[Page 55682]]

FOR FURTHER INFORMATION CONTACT: Mr. Richard Monschke, Aerospace 
Engineer, Rotorcraft Standards Staff, FAA, Rotorcraft Directorate, 2601 
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5116, fax 
(817) 222-5961.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications should identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 95-SW-01-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Office of the Assistant Chief Counsel, Attention: Rules 
Docket No. 95-SW-01-AD, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 
76137.

Discussion

    The Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, recently notified the FAA that an 
unsafe condition may exist on Eurocopter France Model SA-365N, N1, and 
N2 helicopters. The DGAC advises that the forward passenger doors may 
be lost in flight due to the failure of the manufacturer to install the 
appropriate number of spring pins in the door jettison mechanism.
    Eurocopter France has issued Eurocopter Service Bulletin SA 365, 
No. 01.38, dated January 31, 1994, which generally applies to all model 
SA-365 helicopters except for the SA-365C, that specifies an inspection 
of the door jettison systems to detemine if the handle shafts are 
locked to the jettison systems. If the inspection indicates the handle 
shafts are locked to the jettison systems, the proposal would require 
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, the proposal would require 
replacement of the sheared spring pin with two spring pins. The DGAC 
classified this service bulletin as mandatory and issued Airworthiness 
Directive 94-052-035(B), dated March 2, 1994, in order to assure the 
continued airworthiness of these helicopters in France.
    This helicopter model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. The FAA has examined the findings of 
the DGAC, reviewed all available information, and determined that AD 
action is necessary for products of this type design that are 
certificated for operation in the United States.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other Eurocopter France Model SA-365N, N1, and N2 
helicopters of the same type design registered in the United States, 
the proposed AD would require, within 30 days after the effective date 
of the AD, an inspection of the door jettison systems to detemine if 
the handle shafts are locked to the jettison systems. If the inspection 
indicates the handle shafts are locked to the jettison systems, the 
proposed AD would 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 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, the proposal would require, before further 
flight, replacement of the sheared spring pin with two spring pins. 
This proposal 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 would 
be required to be accomplished in accordance with the service bulletin 
described previously.
    The FAA estimates that 27 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 8 work 
hours per helicopter to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Required parts would cost 
approximately $230 per helicopter. Based on these figures, the total 
cost impact of the proposed AD on U.S. operators is estimated to be 
$19,170.
    The regulations proposed herein would 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting 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.

The Proposed Amendment

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

[[Page 55683]]


PART 39--AIRWORTHINESS DIRECTIVES -

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 USC 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended]

    Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

Societe Nationale Industrielle Aerospatiale and Eurocopter France 
(Eurocopter France): 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, 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, in accordance with paragraph 1C1 of Eurocopter Service 
Bulletin (SB) SAA365, No. 01.38, dated January 31, 1994. Based on 
the results of this procedure, perform the following as appropriate: 
-
    (1) If the door jettison handle shaft is locked to the jettison 
system,
    (i) Install the snapwire (annealed copper safety wire, black 
enameled, 0.3mm diameter) on each door jettison handle in accordance 
with paragraph 1C2(a) of SB SA 365, No. 01.38, dated January 31, 
1994.
    (ii) Within 500 hours time-in-service (TIS) after the effective 
date of this AD, in accordance with paragraphs 1C3 and 1C3(a) of SB 
SA 365, No. 01.38, dated January 31, 1994, accomplish the following:
    (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 in 
accordance with paragraphs 1C3 and 1C3(b) of SB SA 365, No. 01.38, 
dated January 31, 1994:
    (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.
    (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 2: 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 
Secs. 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.

    Issued in Fort Worth, Texas, on October 26, 1995.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 95-27203 Filed 11-1-95; 8:45 am]
BILLING CODE 4910-13-U