[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]
=======================================================================
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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).
----------------------------------------------------------------------------------------------------------------
For . . . Then . . . Or . . . Or . . .
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------
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