[Federal Register Volume 70, Number 48 (Monday, March 14, 2005)]
[Rules and Regulations]
[Pages 12408-12410]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-4807]


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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]
BILLING CODE 4910-13-P