AD Amdt-39-9239

[Federal Register Volume 60, Number 101 (Thursday, May 25, 1995)]
[Rules and Regulations]
[Pages 27684-27686]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 95-12607]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-SW-09-AD; Amendment 39-9239; AD 95-11-05]


Airworthiness Directives; Societe Nationale Industrielle 
Aerospatiale and Eurocopter France Model AS-355 E, F, F1, F2, and N 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to Societe Nationale Industrielle Aerospatiale and 
Eurocopter France (Eurocopter France) Model AS-355 E, F, F1, F2, and N 
helicopters. This action requires a check to ensure that the main 
gearbox (MGB) oil pressure warning light illuminates during each 
shutdown of the helicopter engine until the MGB oil pressure switch 
(switch) is removed and replaced. This amendment is prompted by a 
malfunction of the MGB switch. This condition, if not corrected, could 
result in failure to detect a loss of oil pressure, loss of the MGB, 
loss of power to the main rotor system, and subsequent loss of control 
of the helicopter.

DATES: Effective June 9, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 9, 1995.
    Comments for inclusion in the Rules Docket must be received on or 
before July 24, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Assistant Chief Counsel, Attention: 
Rules Docket No. 95-SW-09-AD, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas 76137.
    The service information referenced in this AD 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; or at the Office of the Federal Register, 800 North Capitol 
Street, NW., suite 700, Washington, DC.

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

SUPPLEMENTARY INFORMATION: The Direction Generale De L'Aviation Civile, 
which is the airworthiness authority for France, has notified the FAA 
that an unsafe condition may exist on Eurocopter France Model AS-355 E, 
F, F1, F2, and N helicopters. The Direction Generale De L'Aviation 
Civile advises that a possible malfunction of the MGB switch, part 
number (P/N) 704A37-721-082 (S1130-021-082), modification number 
350A07-7141, was reported by the manufacturer.
    Eurocopter France has issued Eurocopter Service Bulletin AS 355 No. 
01.39, Revision 1, dated April 21, 1994, which specifies a check each 
time the rotor is stopped to ensure that the MGB oil pressure warning 
light illuminates, and removal of the MGB switch, P/N 704A37-721-082 
(S1130-021-082), modification number 350A07-7141, and replacement with 
an airworthy MGB switch. The Direction Generale De L'Aviation Civile 
classified this service bulletin as mandatory and issued AD 94-088-
050(B) in order to assure the continued airworthiness of these 
helicopters in France.
    These helicopter models are manufactured in France and are 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 Direction Generale De L'Aviation 
Civile has kept the FAA informed of the situation described above. The 
FAA has examined the findings of the Direction Generale De L'Aviation 
Civile, 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 AS-355 E, F, F1, F2, 
and N helicopters of the same type design registered in the United 
States, this AD is being issued to prevent an undetected loss of oil 
pressure, loss of the MGB, loss of power to the main rotor system, and 
subsequent loss of control of the [[Page 27685]] helicopter. This AD 
requires a check during each shutdown of the helicopter engine to 
ensure that the MGB oil pressure warning light illuminates, and removal 
of the MGB switch, P/N 704A37-721-082 (S1130-021-082), modification 
number 350A07-7141, and replacement with MGB switch, P/N 704A37-721-089 
(S1130-021-089), modification number 350A07-7152, or Jaeger MGB switch, 
P/N 704A37-721-014 (068651.54/350A32-3134-00), within 30 days after the 
effective date of this AD. The owner/operator check does not require 
the use of tools, precision measuring equipment, training, pilot 
logbook endorsements, or the use of technical data not contained in the 
AD. Additionally, this owner/operator check is considered part of the 
normal engine shutdown checks. This check may be performed by an owner/
operator holding at least a private pilot certificate and must be 
entered into the aircraft records showing compliance with this AD in 
accordance with sections 43.11 and 91.417(a)(2)(v) of the Federal 
Aviation Regulations. An undetected loss of oil pressure could result 
in a forced autorotative landing due to loss of power to the main rotor 
system. Due to the short compliance time and the criticality of the MGB 
switch to detect a loss of oil pressure, this AD is being issued 
immediately. The actions are required to be accomplished in accordance 
with the service bulletin described previously.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 95-SW-09-AD.'' The postcard will be date stamped and 
returned to the commenter.
    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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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, Incorporation by 
reference, 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 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR section 11.89.


Sec. 39.13  [Amended]

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

95-11-05  Societe Nationale Industrielle Aerospatiale and Eurocopter 
France (Eurocopter France): Amendment 39-9239. Docket No. 95-SW-09-
AD.

    Applicability: Model AS-355 E, F, F1, F2, and N helicopters, 
with main gearbox (MGB) oil pressure switch (switch), part number 
(P/N) 704A37-721-082 (S1130-021-082), modification number 350A07-
7141, 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 
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 (d) 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 an undetected loss of oil pressure, loss of 
the MGB, loss of power to the main rotor system, and subsequent loss 
of control of the helicopter, accomplish the following:
    (a) Until the MGB switch installation required by paragraph (c) 
of this AD is accomplished, during each shutdown of the helicopter 
engine, check to ensure that the MGB pressure warning light 
illuminates. If it does not illuminate, before further flight, 
replace the MGB switch in accordance with paragraph (c) of this AD.
    (b) The operational check required by paragraph (a) of this AD 
may be performed by an owner/operator holding at least a private 
pilot certificate and must be entered into the aircraft records 
showing compliance with this AD in accordance with 14 CFR sections 
43.11 and 91.417(a)(2)(v).
    (c) Within 30 days after the effective date of this AD, remove 
the MGB switch, P/N 704A37-721-082 (S1130-021-082), modification 
number 350A07-7141, and replace with MGB switch, P/N 704A37-721-089 
(S1130-021-089), modification number 350A07-7152, or Jaeger MGB 
switch, P/N 704A37-721-014 (068651.54/350A32-3134-00) in accordance 
with paragraph CC(1) of [[Page 27686]] Eurocopter Service Bulletin 
AS 355, No. 01.39, Revision 1, dated April 21, 1994.

    Note 2: The MGB switch P/N is engraved on the MGB switch casing.

    (d) 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.

    (e) The check, removal, and replacement shall be done in 
accordance with Eurocopter Service Bulletin AS 355 No. 01.39, 
Revision 1, dated April 21, 1994. 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 
American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, 
Texas 75053-4005. Copies may be inspected at the FAA, Office of the 
Assistant Chief Counsel, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas 76137; or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.
    (f) This amendment becomes effective on June 9, 1995.

    Issued in Fort Worth, Texas, on May 17, 1995.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 95-12607 Filed 5-24-95; 8:45 am]
BILLING CODE 4910-13-P]