[Federal Register: March 8, 2005 (Volume 70, Number 44)]
[Proposed Rules]
[Page 11166-11168]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr08mr05-19]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20512; Directorate Identifier 2004-SW-35-AD]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model EC 155B,
EC155B1, SA-365N, SA-365N1, AS-365N2, and AS 365 N3 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes superseding an existing airworthiness
directive (AD) that applies to Eurocopter France (Eurocopter) Model EC
155B, SA-365N and N1, AS-365N2, and AS 365 N3 helicopters. That AD
currently requires inspecting the hydraulic brake hose (hose) for
crazing, pinching, distortion, or leaks at the torque link hinge and
replacing the hose, if necessary. That AD also requires inspecting the
hose and the emergency flotation gear pipe to ensure adequate
clearance, and adjusting the landing gear leg, if necessary. This
action would require the same actions as the existing AD and would add
a model to the applicability. This proposal is prompted by notification
by the manufacturer and the European Authority that another affected
model helicopter, the Model EC155B1, may have the same unsafe condition
and should be added to the existing AD. The actions specified by the
proposed AD are intended to prevent failure of a hose, resulting in
failure of hydraulic pressure to the brakes on the affected landing
gear wheel, and subsequent loss of control of the helicopter during a
run-on landing.
DATES: Comments must be received on or before May 9, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed 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,
[[Page 11167]]
400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
You may get the service information identified in this proposed AD
from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie,
Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527.
You may examine the comments to this proposed AD in the AD docket
on the Internet at http://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT: Uday Garadi, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Safety Management Group, Fort Worth, Texas
76193-0110, telephone (817) 222-5123, fax (817) 222-5961.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written data, views, or arguments
regarding this proposed AD. Send your comments to the address listed
under the caption ADDRESSES. Include the docket number ``FAA-2005-
20512, Directorate Identifier 2004-SW-35-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed 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 proposed rulemaking. 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 or
signed 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.
Examining the Docket
You may examine the docket that contains the proposed AD, any
comments, and other information in person at the Docket Management
System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone 1-800-
647-5227) is located at the plaza level of the Department of
Transportation NASSIF Building in Room PL-401 at 400 Seventh Street,
SW., Washington, DC. Comments will be available in the AD docket
shortly after the DMS receives them.
Discussion
On August 26, 2003, we issued AD 2003-18-03, Amendment 39-13294 (68
FR 52832, September 8, 2003). That AD requires, within the next 10
hours time-in-service (TIS), inspecting the hose for crazing, pinching,
distortion, or leaks at the torque link hinge and replacing the hose
before further flight, if necessary. AD 2003-18-03 also requires, at
the next 100-hour TIS inspection, inspecting the hose and the emergency
flotation gear pipe to ensure adequate clearance, and adjusting the
landing gear leg, if necessary. That action was prompted by a report of
a hose compression due to interference with a clamp that attaches the
emergency flotation gear pipe. The requirements of that AD are intended
to prevent failure of a hose, resulting in failure of hydraulic
pressure to the brakes on the affected landing gear wheel, and
subsequent loss of control of the helicopter during a run-on landing.
Since issuing that AD, the manufacturer has issued a revision to
its Alert Service Bulletin No. 32A004 to now include the Model EC155B1
helicopters that we did not include in the applicability of that AD.
The Direction Generale De L'Aviation Civile (DGAC), the
airworthiness authority for France, has notified the FAA that an unsafe
condition may exist on Eurocopter Model EC 155 B1 helicopters as well
as the other affected model helicopters. The DGAC has advised in AD No.
F-2004-099, dated July 7, 2004, that a report of a wheel brake hose
compression due to interference with a clamp that attaches the
emergency flotation gear pipe led to the issue of AD No. 2002-475-007,
which defined measures applicable to EC 155 version B aircraft. DGAC AD
No. 2002-475-007 was cancelled by its Revision 1, and the DGAC issued
AD No. F-2004-099, dated July 7, 2004, which supersedes and covers the
requirements of AD 2002-475-007, extends its affectivity to EC 155
version B1 aircraft, and refers to revised service information, with no
change to the technical content. The DGAC issued that AD after
Eurocopter issued Alert Service Bulletin No. 32A004, Revision 1, dated
June 16, 2004. The revised service bulletin added the Eurocopter Model
EC155B1 to it's applicability but didn't change any technical content.
Eurocopter has also replaced Alert Telex No. 32.00.09, dated July
31, 2002, with Alert Service Bulletin No. 32.00.09, dated October 27,
2003. The service bulletin applies to Eurocopter Model SA-365N, SA-
365N1, AS-365N2, and AS 365 N3 helicopters and was issued to replace
Alert Telex No. 32.00.09, dated July 31, 2002, and contained no
technical changes. The DGAC classified this service bulletin as
mandatory and issued AD No. F-2002-474-058 R1, dated March 3, 2004. The
proposed AD contains references to both of these revised documents.
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 us informed of the
situation described above. We have examined the findings of the DGAC,
reviewed all available information, and determined that AD action is
necessary for products of these type designs that are certificated for
operation in the United States.
This previously described unsafe condition is likely to exist or
develop on other helicopters of the same type designs. Therefore, the
proposed AD would supersede AD 2003-18-03. The proposed AD would add
the Eurocopter Model EC155B1 helicopters to the applicability and
continue to require, within the next 10 hours TIS, inspecting the hose
for crazing, pinching, distortion, or leaks at the torque link hinge
and replacing the hose before further flight, if necessary. The
proposed AD would also continue to require, at the next 100-hour TIS
inspection, inspecting the hose and the emergency flotation gear pipe
to ensure adequate clearance, and adjusting the landing gear leg, if
necessary. The inspections would have to be done in accordance with the
alert service bulletins described previously.
We estimate that this proposed AD would affect 48 helicopters of
U.S. registry. It would take approximately 5 work hours per helicopter
to accomplish each inspection and 5 work hours to replace any parts, as
necessary. The average labor rate is $65 per work hour. Required parts
would cost approximately $459 for the hose; if replacing the hose on
two sides is required, the cost would be approximately $918. Based on
these figures, the total cost impact of the proposed AD on U.S.
operators is estimated to be $1,568 per helicopter, or $56,448 for the
entire fleet, assuming 75 percent of the fleet (36 helicopters) is
equipped with emergency flotation gear, that one inspection is done,
and that the hose on two sides is replaced on those 36 helicopters).
[[Page 11168]]
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. Additionally, this proposed
AD would 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 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. 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 a draft economic evaluation of the estimated costs to
comply with this proposed AD. See the DMS to examine the draft economic
evaluation.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
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:
PART 39--AIRWORTHINESS DIRECTIVES
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]
2. Section 39.13 is amended by removing Amendment 39-13294 (68 FR
52832, September 8, 2003), and by adding a new airworthiness directive
(AD), to read as follows:
Eurocopter France: Docket No. FAA-2005-20512; Directorate Identifier
2004 SW-35. Supersedes AD 2003-18-03, Amendment 39-13294, Docket No.
2002-SW-53-AD.
Applicability: Model EC 155B, EC155B1, SA-365N, SA-365N1, AS-
365N2, and AS 365 N3 helicopters, with emergency flotation gear
installed, certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of a hydraulic brake hose (hose), resulting
in failure of hydraulic pressure to the brakes on the affected
landing gear wheel and subsequent loss of control of the helicopter
during a run-on landing, accomplish the following:
(a) Within 10 hours time-in-service (TIS), inspect the hose for
crazing, pinching, distortion, or leaks as illustrated in Area A of
Figure 1 of Eurocopter Alert Service Bulletin No. 32.00.09, dated
October 27, 2003 (ASB No. 32.00.09), for Model SA-365N and N1, AS-
365N2, and AS 365 N3 helicopters, and Eurocopter Alert Service
Bulletin No. 32A004, Revision 1, dated June 16, 2004 (ASB No.
32A004R1), for Model EC 155B and EC155B1 helicopters.
(b) If crazing, pinching, distortion, or leaks exist, replace
the hose with an airworthy hose before further flight.
(c) At the next 100-hour TIS inspection, inspect the hose and
the emergency flotation gear pipe to ensure adequate clearance and
adjust the landing gear leg, if necessary, in accordance with the
Operational Procedure, paragraph 2.B.2., of ASB No. 32.00.09 or ASB
No. 32A004R1, as applicable.
(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.
Note: The subject of this AD is addressed in Direction Generale
De L'Aviation Civile (France) AD No. F-2002-474-058 R1, dated March
3, 2004 and AD No. F-2004-099, dated July 7, 2004.
Issued in Fort Worth, Texas, on March 1, 2005.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 05-4406 Filed 3-7-05; 8:45 am]
BILLING CODE 4910-13-P