[Federal Register: March 14, 2005 (Volume 70, Number 48)]
[Rules and Regulations]
[Page 12408-12410]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14mr05-5]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-SW-47-AD; Amendment 39-14009; AD 2005-06-01]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model EC 155B and EC
155B1 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) for
Eurocopter France (Eurocopter) Model EC 155B and EC 155B1 helicopters
that requires inspecting the chamfer of the stop on the cabin sliding
doors (doors) and installing an airworthy stop if the chamfer exceeds a
certain length; and prior to each flight, visually checking the door to
determine if it is correctly locked in the open position before flying
with the doors open, and checking the locking indicator light and the
position of the door handles before flying with the doors closed. This
amendment also requires revising the Limitations Section of the
Rotorcraft Flight Manual (RFM) to prohibit the opening or closing of a
cabin sliding door at airspeeds of 40 or greater knots indicated
airspeed (KIAS). This amendment is prompted by a report of a door
separating from a helicopter during flight. The actions specified by
this AD are intended to prevent separation of a door during flight and
damage to the helicopter, resulting in a forced landing or loss of
control of the helicopter.
DATES: Effective April 18, 2005.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 18, 2005.
ADDRESSES: The service information referenced in this AD may be
obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand
Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-
3527. This information may be examined at the FAA, Office of the
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort
Worth, Texas.
FOR FURTHER INFORMATION CONTACT: Charles Harrison, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group,
Fort Worth, Texas 76193-0111, telephone (817) 222-5128, fax (817) 222-
5961.
SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to
include an AD for Eurocopter Model EC 155B and EC 155B1 helicopters was
published in the Federal Register on August 19, 2004 (69 FR 51402).
That action proposed to require, before further flight, revising the
Limitations Section of the RFM to prohibit opening or closing the cabin
doors except at speeds of less than 40 KIAS; within the next 50 hours
TIS, inspecting the chamfer of the stop of the lower rail aft fitting
of the doors, and if the chamfer is greater than 2mm in length,
installing an airworthy stop. That action also proposed to require;
prior to each flight with a door open, visually checking that the door
is correctly locked in the open position; and prior to flight with a
door closed, checking that the locking indicator light on the
instrument panel is ``off'' when the door is closed, that the door
handles are in the correct closed position when the door is locked, and
that the lower locking pin is correctly positioned in its catch. These
closed-door checks were proposed to be required until a chamfer that is
2mm or less in length is installed and, in accordance with MOD 0753C48,
the mounting support plates are modified and the door micro-switches
are adjusted. It was proposed that the modification would be
accomplished in accordance with the manufacturer's service information.
It was also proposed that the owner/operator (pilot) holding at
least a private pilot certificate may perform the visual checks
required by paragraphs (c) and (d) of the proposed AD and must enter
compliance with those paragraphs into the aircraft maintenance records
in accordance with 14 CFR 43.11 and 91.417(a)(2)(v). The AD would allow
a pilot to perform these checks because they involve only visual checks
to ensure that the cabin sliding doors are correctly locked in the open
or closed position, and can be performed equally well by a pilot or a
mechanic.
The Direction Generale De L'Aviation Civile (DGAC), the
airworthiness authority for France, notified the FAA that an unsafe
condition may exist on Model EC 155B and EC 155B1 helicopters. The DGAC
advises that they have issued an AD following the loss in flight of a
cabin sliding door.
Eurocopter issued Alert Service Bulletin No. 52A015, dated
September 8, 2003, which specified a modification (MOD 0753C48) to the
micro switch support, and an adjustment to the micro switch to ensure
lighting of the instrument panel ``DOORS'' light in the event of
insufficient engagement of the cabin sliding door locking pin in its
catch. The FAA did not mandate compliance with this alert service
bulletin.
Eurocopter has also issued Alert Telex No. 52A013, Revision 1,
dated September 24, 2003, which specifies:
Within the next 50 hours time-in-service (TIS), inspecting
the length of the chamfer on the stop of the lower rail aft fitting of
the cabin sliding doors;
Prior to flight with a cabin sliding door open, visually
checking that the door is correctly locked in the open position;
Prior to flight with a cabin sliding door closed, checking
that the locking indicator light on the instrument panel is off when
the door is closed, and when locking the door, checking that the door
handle is in the closed position; and
While in flight, prohibiting the opening or closing of a
cabin sliding door at airspeeds of 40 or greater KIAS.
The DGAC classified this alert telex as mandatory and issued AD No.
F-2003-345 R1, dated November 12, 2003, to
[[Page 12409]]
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 are certificated
for operation in the United States.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposal or the FAA's determination of the cost to the public. The FAA
has determined that air safety and the public interest require the
adoption of the rule as proposed.
This AD is an interim action until modified parts are developed.
Additionally, if a door is opened or closed during flight, in
accordance with the limitations of the RFM, the FAA anticipates that
the appropriate crewmembers will assure that the door is properly
secured.
The FAA estimates that this AD will affect 3 helicopters of U.S.
registry. It will take approximately 1 minute for each check on each
helicopter, 2 work hours per helicopter to install 2 new stops, and 2
work hours to modify each helicopter in accordance with MOD 0753C48, at
an average labor rate of $65 per work hour. Required parts will cost
approximately $1,125 ($375 per helicopter). Based on these figures, we
estimate the total cost impact of the AD on U.S. operators to be $
3,855 for the entire fleet, assuming 600 checks per helicopter and
assuming that two stops are replaced on each helicopter, each
helicopter is modified in accordance with MOD 0753C48, and the time to
make the one-time revision to the RFM is negligible.
Regulatory Findings
The regulations adopted herein 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. Therefore, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
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, Incorporation by
reference, 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:
2005-06-01 Eurocopter France: Amendment 39-14009. Docket No. 2003-
SW-47-AD.
Applicability: Model EC 155B and EC 155B1 helicopters with cabin
sliding doors, part number (P/N) 365A82-1064-02 (left-hand door) and
P/N 365A82-1064-03 (right-hand door) and stop, P/N 365A25-8085-21,
installed, certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent separation of a door during flight and damage to the
helicopter, resulting in a forced landing or loss of control of the
helicopter, accomplish the following:
(a) Before further flight, revise the Limitations Section of the
Rotorcraft Flight Manual (RFM) permitting the opening or closing of
the cabin sliding doors only at speeds of less than 40 knots
indicated airspeed.
(b) Within 50 hours time-in-service, inspect the length of the
chamfer on the stop of the lower rail aft fitting on each cabin
sliding door (door), and if the chamfer is more than 2mm in length,
install an airworthy stop in accordance with paragraph 2.B.,
Operational Procedure, of Eurocopter Alert Telex No. 52A013,
Revision 1, dated September 24, 2003.
Note 1: The inspection required by paragraph (b) of this AD has
already been accomplished for all Model EC 155B1 helicopters prior
to delivery.
(c) Before each flight with a door open, check that each open
door is locked in the ``open'' position with the upper roller in its
rail and the door open locking latch engaged.
(d) Before each flight with a door closed, check that:
(1) The locking indicator light on the instrument panel is
``off,''
(2) The door handle is in the correct ``closed'' position, and
(3) The lower locking pin is positioned in its catch.
Note 2: If the door is correctly closed and latched, when viewed
from the outside, the door handle will be flush with the profile of
the housing and the aft lower corner of the door will be flush with
the profile of the fuselage; when viewed from the inside, the door
handle will be positioned opposite the locking indicator with no gap
between the structure seal and the aft lower sealing surface of the
door.
Note 3: If the door is closed and the lower locking pin is
outside its catch, when viewed from the outside, the aft lower
corner of the door is approximately 15 to 20mm from the fuselage;
when viewed from the inside, the aft lower corner of the door is
approximately 10 to 15mm from the fuselage.
(e) An owner/operator (pilot) holding at least a private pilot
certificate may perform the visual checks required by paragraphs (c)
and (d) of this AD and must enter compliance with those paragraphs
into the aircraft maintenance records in accordance with 14 CFR
43.11 and 91.417(a)(2)(v).
(f) After the stops of the lower rail aft fitting with a chamfer
2mm or less in length are installed and in accordance with MOD
0753C48, the mounting plate supports are modified and the door
micro-switches are adjusted, the checks required by paragraph (d) of
this AD are no longer required.
(g) 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,
[[Page 12410]]
Rotorcraft Directorate, FAA, for information about previously
approved alternative methods of compliance.
(h) The modification shall be done in accordance with Eurocopter
Alert Telex No. 52A013, Revision 1, dated September 24, 2003. The
Director of the Federal Register approved this incorporation by
reference 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, telephone (972) 641-
3460, fax (972) 641-3527. Copies may be inspected at the FAA, Office
of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room
663, Fort Worth, Texas; or at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
(i) This amendment becomes effective on April 18, 2005.
Note 4: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) AD No. F-2003-345-R1, dated
November 12, 2003.
Issued in Fort Worth, Texas, on March 4, 2005.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 05-4807 Filed 3-11-05; 8:45 am]
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