[Federal Register Volume 69, Number 160 (Thursday, August 19, 2004)]
[Rules and Regulations]
[Pages 51358-51362]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-18438]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-18850; Directorate Identifier 2004-SW-19-AD; 
Amendment 39-13771; AD 2004-16-15]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS-365N2, AS 
365 N3, EC 155B, EC155B1, SA-365N and N1, and SA-366G1 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) for 
the specified Eurocopter France (Eurocopter) helicopters. This action 
requires inspecting the main gearbox (MGB) baseplate for a crack and 
replacing the MGB if a crack is found in the MGB base plate. This 
amendment is prompted by the discovery of a crack in a MGB base plate. 
The actions specified in this AD are intended to detect a crack in a 
MGB base plate and prevent failure of one of the MGB attachment points 
to the frame, which could result in severe vibration and subsequent 
loss of control of the helicopter.

DATES: Effective September 3, 2004.
    Comments for inclusion in the Rules Docket must be received on or 
before October 18, 2004.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically;
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically;
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590;
     Fax: (202) 493-2251; or
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the Dockets

    You may examine the docket that contains the AD, any comments, and 
other information on the Internet at http://dms.dot.gov, or in person 
at the Docket Management System (DMS) Docket Offices between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The Docket 
Office (telephone (800) 647-5227) is located on the plaza level of the 
Department of Transportation Nassif Building at the street address 
stated in the ADDRESSES section. Comments will be available in the AD 
docket shortly after the DMS receives them.

FOR FURTHER INFORMATION CONTACT: Ed Cuevas, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Safety Management Group, Fort Worth, Texas 
76193-0111, telephone (817) 222-5355, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for 
Eurocopter Model AS-365N2, AS 365 N3, EC 155B, EC155B1, SA-365N and N1, 
and SA-366G1 helicopters. This action requires visually inspecting the 
MGB for a crack in the MGB base plate, part number (P/N) 366A32-1062-03 
or P/N 366A32-1062-06, close to the attachment hole using a 10x or 
higher magnifying glass. Stripping paint from the inspection area is 
also required, but only before the initial inspection. This amendment 
is prompted by the discovery of a crack in the MGB base plate of a MGB 
installed in a Model AS-365 N2 helicopter. The cause of the crack is 
under investigation, therefore, this AD is an interim action until the 
cause of the crack can be determined. The crack was located very close 
to the attachment points of one of the laminated pads, and it 
propagated to the inside of the MGB base plate and then continued into 
the MGB casing. This condition, if not detected, could result in 
failure of one of the MGB attachment points to the frame, which could 
result in severe vibration and subsequent loss of control of the 
helicopter.
    The Direction Generale De L'Aviation Civile (DGAC), the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may exist on Eurocopter Model SA 365 N, N1, SA 366 G1, AS 365 
N2, N3, and EC 155 B and B1 helicopters. The DGAC advises of the 
discovery of a crack on the MGB base plate of a Model AS 365 N2 
helicopter.
    Eurocopter has issued Alert Telexes:
     No. 05.00.45, applicable to Model 365 N, N1, N2, and N3 
helicopters;
     No. 05.29, applicable to Model 366 G1 helicopters; and
     No. 05A005, applicable to Model EC 155 B and B1 
helicopters, all dated February 5, 2004. These alert telexes specify 
visually inspecting the MGB base plate for absence of cracks. In 
addition, the alert telexes state that a 10x magnifying glass can be 
used to facilitate the crack inspection. Also, if in doubt about the 
existence of a crack, the alert telexes specify inspecting for a crack 
using a dye-penetrant crack detection inspection. The DGAC classified 
these alert telexes as mandatory and issued AD No. UF-2004-023(A), 
dated February 6, 2004, and AD No. F-2004-023, dated March 3, 2004, to 
ensure 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 
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the 
applicable bilateral 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 these type designs that

[[Page 51359]]

are certificated for operation in the United States.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type design. Therefore, this AD is being issued 
to detect a crack in the MGB base plate and prevent failure of one of 
the MGB attachment points to the frame, which could result in severe 
vibration and subsequent loss of control of the helicopter. This AD 
requires initial and repetitive inspections of the MGB base plate for 
cracking at various short time intervals until its cause can be 
determined. Various compliance times are required depending on the 
helicopter model. The short compliance times involved are required 
because the previously described critical unsafe condition can 
adversely affect the controllability or structural integrity of the 
helicopter. Therefore, since initial and repetitive inspections of the 
MGB base plate for cracking are required at short time intervals, this 
AD must be issued immediately.
    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.
    We estimate that this AD will affect 142 helicopters and that the 
initial inspection will take approximately 0.5 work hour. Each 
recurring inspection will take approximately 0.25 work hour, and 
replacing the MGB, if necessary, will take approximately 4 work hours 
to accomplish, all at an average labor rate of $65 per work hour. It 
will cost approximately $25,000 to repair a cracked MGB base plate. 
Based on these figures, the total cost impact of the AD on U.S. 
operators is estimated to be $138,067, assuming that each of the 135 
Model AS 365 and SA 366 helicopters are inspected 40 times (the initial 
inspection plus 39 recurring inspections) and each of the 7 Model EC 
155 helicopters are inspected 200 times (the initial inspection plus 
199 recurring inspections), and one cracked MGB base plate is found 
requiring the replacement of one MGB. This estimate also assumes that a 
replacement MGB will not need to be purchased while a previously-
installed MGB is being repaired.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any written data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2004-18850; 
Directorate Identifier 2004-SW-19-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD. We will consider 
all comments received by the closing date and may amend the AD in light 
of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of our docket 
Web site, you can find and read the comments to any of our dockets, 
including the name of the individual who sent the comment. You may 
review the DOT's complete Privacy Act Statement in the Federal Register 
published on April 11, 2000 (65 FR 19477-78), or you may visit http://dms.dot.gov.
    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect 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.
    For the reasons discussed above, I certify that the 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. 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.
    We prepared an economic evaluation of the estimated costs to comply 
with this AD. See the DMS to examine the economic evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
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

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2004-16-15 Eurocopter France: Amendment 39-13771. Docket No. FAA-
2004-18850; Directorate Identifier 2004-SW-19-AD

    .Applicability: Eurocopter France Model AS-365N2, AS 365 N3, EC 
155B, EC155B1, SA-365N and N1, and SA-366G1 helicopters with a main 
gearbox (MGB) base plate, part number (P/N) 366A32-1062-03 or P/N 
366A32-1062-06, installed, certificated in any category.
    Compliance: Required as indicated in the following table and 
before installing a replacement main gearbox (MGB).

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              For . . .                       Then . . .                Or . . .                 Or . . .
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Model SA-365N and N1, and Model SA-    If a MGB is installed    If a MGB is installed    If a MGB is installed
 366G1 helicopters.                     that has less than       that has 9,900 or more   that is overhauled or
                                        9,900 cycles and has     cycles and has never     repaired, before
                                        never been overhauled    been overhauled or       further flight, unless
                                        or repaired. On or       repaired, before         accomplished
                                        before accumulating      further flight, unless   previously, and
                                        9,900 cycles, unless     accomplished             thereafter, at
                                        accomplished             previously, and          intervals not to
                                        previously, and          thereafter, at           exceed 15 hours TIS.
                                        thereafter, at           intervals not to
                                        intervals not to         exceed 15 hours TIS.
                                        exceed 15 hours time-
                                        in-service (TIS).

[[Page 51360]]

 
Model AS-365N2 and AS 365 N3           If a MGB is installed    If a MGB is installed    If a MGB is installed
 helicopters.                           that has less than       that has 7,300 or more   that has been
                                        7,300 cycles and has     cycles and has never     overhauled or
                                        never been overhauled    been overhauled or       repaired, before
                                        or repaired, on or       repaired, before         further flight, and
                                        before accumulating      further flight, and      thereafter, at
                                        7,300 cycles, unless     thereafter, at           intervals not to
                                        accomplished             intervals not to         exceed 15 hours TIS.
                                        previously, and          exceed 15 hours TIS.
                                        thereafter, at
                                        intervals not to
                                        exceed 15 hours TIS.
Model EC 155B and EC155B1 helicopters  If a MGB base plate is   If a MGB base plate is
                                        installed that has       installed that has
                                        less than 2,600          2,600 or more cycles,
                                        cycles, no later than    unless accomplished
                                        2,600 cycles, unless     previously, before
                                        accomplished             further flight, and
                                        previously, and          thereafter, before the
                                        thereafter, before the   first flight of each
                                        first flight of each     day and on or before
                                        day and on or before     reaching each 9 hours
                                        reaching each 9 hours    TIS interval during
                                        TIS interval during      the day .
                                        the day.
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One cycle equates to one helicopter landing in which a landing gear touches the ground.

    To detect a crack in the MGB base plate and prevent failure of a 
MGB attachment point to the frame, which could result in severe 
vibration and subsequent loss of control of the helicopter:
    (a) Before the initial inspection at the time indicated in the 
compliance table, strip the paint from area ``D'' on both sides 
(``B'' and ``C'') of the MGB base plate as depicted in Figure 1.
BILLING CODE 4910-13-P

[[Page 51361]]

[GRAPHIC] [TIFF OMITTED] TR19AU04.035

    (b) At the times indicated in the compliance table, inspect area 
``D'' of the MGB base plate for a crack using a 10x or higher 
magnifying glass.

    Note 1: Eurocopter France Alert Telex No. 05.00.45, applicable 
to Model AS-365N2, AS 365 N3, SA-365N and SA-365N1 helicopters; 
Alert Telex No. 05.29, applicable to Model SA-366G1 helicopters, and 
Alert Telex No. 05A005, applicable to Model EC 155B and EC155B1 
helicopters, pertain to the subject of this AD. All three alert 
telexes are dated February 5, 2004.

    (c) If a crack is found in a MGB base plate, remove and replace 
the MGB with an airworthy MGB before further flight.
    (d) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Safety Management Group, Rotorcraft Directorate, FAA, 
for information about previously approved alternative methods of 
compliance.

[[Page 51362]]

    (e) This amendment becomes effective on September 3, 2004.

    Note 2: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD No. UF-2004-023(A), dated 
February 6, 2004, and AD No. F-2004-023, dated March 3, 2004.


    Issued in Fort Worth, Texas, on August 4, 2004.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 04-18438 Filed 8-18-04; 8:45 am]
BILLING CODE 4910-13-C