Airworthiness Directives; Eurocopter France Model EC 155B and EC 155B1 Helicopters, 12408-12410 [05-4807]
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12408
Federal Register / Vol. 70, No. 48 / Monday, March 14, 2005 / Rules and Regulations
Alternative Methods of Compliance
(AMOCs)
(g) The Manager, International Branch,
ANM–16, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
Related Information
(h) German airworthiness directive D–
2004–003, dated January 8, 2004, also
addresses the subject of this AD.
Material Incorporated by Reference
(i) You must use Dorner Service Bulletin
SB–328J–32–169, including the Price/
Material Information Sheet, dated November
20, 2002, to perform the actions that are
required by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approves the incorporation by
reference of these documents in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. For
copies of the service information, contact
AvCraft Aerospace GmbH, P.O. Box 1103, D–
82230 Wessling, Germany. For information
on the availability of this material at the
National Archives and Records
Administration (NARA), call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
You may view the AD docket at the Docket
Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW.,
room PL–401, Nassif Building, Washngton,
DC.
Issued in Renton, Washington, on February
28, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–4413 Filed 3–11–05; 8:45 am]
BILLING CODE 4910–13–M
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
Federal Aviation
Administration, DOT.
ACTION: Final rule.
AGENCY:
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
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15:26 Mar 11, 2005
Jkt 205001
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-
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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-inservice (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
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Federal Register / Vol. 70, No. 48 / Monday, March 14, 2005 / Rules and Regulations
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.
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.
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
I
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15:26 Mar 11, 2005
Jkt 205001
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
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:
I
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.
§ 39.13
[Amended]
2. Section 39.13 is amended by adding
a new airworthiness directive to read as
follows:
I
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-
PO 00000
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12409
hand door) and P/N 365A82–1064–03 (righthand 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,
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Federal Register / Vol. 70, No. 48 / Monday, March 14, 2005 / Rules and Regulations
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: https://
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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–19022; Directorate
Identifier 2004–NM–122–AD; Amendment
39–14007; AD 2005–05–18]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–600, –700, –700C, –800, and
–900 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 737–600, –700, –700C,
–800, and –900 series airplanes. This
AD requires repetitive detailed, low
frequency eddy current, and high
frequency eddy current inspections of
the webs of the aft pressure bulkhead at
body station 1016 for cracks, and
corrective action if necessary. This AD
is prompted by a report of cracks found,
during fatigue testing, at several of the
fastener rows in the web lap splices at
SUMMARY:
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15:26 Mar 11, 2005
Jkt 205001
the dome apex of the aft pressure
bulkhead. We are issuing this AD to
detect and correct fatigue cracks in the
webs of the aft pressure bulkhead,
which could result in rapid
decompression of the airplane.
Comments
This AD becomes effective April
18, 2005.
The incorporation by reference of a
certain publication listed in the AD is
approved by the Director of the Federal
Register as of April 18, 2005.
Request for Repair or Preventative
Modification
DATES:
For service information
identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
Docket: The AD docket contains the
proposed AD, comments, and any final
disposition. You can examine the AD
docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The
Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the U.S. Department of Transportation,
400 Seventh Street, SW., room PL–401,
Washington, DC. This docket number is
FAA–2004–19022; the directorate
identifier for this docket is 2004–NM–
122–AD.
ADDRESSES:
FOR FURTHER INFORMATION CONTACT:
Howard Hall, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6430; fax (425) 917–6590.
The FAA
proposed to amend 14 CFR Part 39 with
an AD for certain Boeing Model 737–
600, –700, –700C, –800, and –900 series
airplanes. That action, published in the
Federal Register on September 7, 2004
(69 FR 54053), proposed to require
repetitive detailed, low frequency eddy
current, and high frequency eddy
current inspections of the webs of the
aft pressure bulkhead at body station
1016 for cracks, and corrective action if
necessary.
SUPPLEMENTARY INFORMATION:
Actions Since Notice of Proposed
Rulemaking (NPRM) Was Issued
Since the NPRM was issued, Boeing
has received a Delegation Option
Authorization (DOA). We have revised
this final rule to delegate the authority
to approve an alternative method of
compliance (AMOC) for any repair
required by this AD to an Authorized
Representative for the Boeing DOA
Organization rather than a Designated
Engineering Representative.
PO 00000
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Fmt 4700
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We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment that has been
submitted on the proposed AD.
The commenter, an operator, requests
that the manufacturer add either repair
instructions or a preventative
modification and task hour estimate for
the respective action to Boeing Service
Bulletin 737–53–1251, dated June 3,
2004. The commenter states that the
service bulletin does not recommend
any repair or terminating action if
cracks are found during inspection of
the aft pressure bulkhead, but instead
specifies contacting the manufacturer if
cracks are found.
Although we agree with the intent of
the commenter’s request, we also know
that variations in the type and degree of
damage at and around the web lap
splices at the dome apex of the aft
pressure bulkhead make it difficult to
develop general repair instructions, or a
preventative modification, that could be
applicable to and effective for all
conditions. Furthermore, the
manufacturer has experience repairing
damage in the area of the web lap
splices of the aft pressure bulkhead and
can assist in developing repairs
appropriate for specific conditions. For
these reasons, we are allowing the
Manager, Seattle Aircraft Certification
Office, FAA, or an Authorized
Representative for the Boeing DOA
Organization to approve repairs in
accordance with paragraph (g) of this
final rule. If general repair instructions
or a preventative modification should be
developed at a later time, and the
service bulletin is revised to include
either of these actions, we will consider
approving the revised service bulletin as
an AMOC to this final rule. Therefore,
no change is necessary to this final rule
in this regard.
Explanation of Editorial Change
For clarification, we have replaced the
word ‘‘listed’’ with ‘‘identified’’ to
specify the applicability in paragraph (c)
of this AD.
Conclusion
We have carefully reviewed the
available data, including the comment
that has been submitted, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously.
We have determined that these changes
will neither increase the economic
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]]>Agencies
[Federal Register Volume 70, Number 48 (Monday, March 14, 2005)]
[Rules and Regulations]
[Pages 12408-12410]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-4807]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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: https://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
