[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
