[Federal Register: January 9, 2004 (Volume 69, Number 6)]
[Rules and Regulations]
[Page 1521-1522]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09ja04-11]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-SW-41-AD; Amendment 39-13428; AD 2004-01-14]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model EC130B4
Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) for
Eurocopter France (Eurocopter) Model EC130B4 helicopters with a certain
air intake cowling attachment fitting (fitting) installed. This action
requires inspecting for broken or cracked forward fittings. If a broken
or cracked fitting is found, inspecting the four center and aft
fittings for cracks is required. Replacing broken fittings or certain
cracked fittings is also required. This amendment is prompted by
reports of cracked and broken fittings; one fitting failed after only
418 hours time-in-service (TIS). This condition, if not corrected,
could result in failure of a forward fitting, an excess load on the
other fittings, which could cause them to crack and break, which could
result in loss of the air intake cowling in flight, and subsequent
damage or loss of control of the helicopter, or both.
DATES: Effective January 26, 2004.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 26, 2004.
Comments for inclusion in the Rules Docket must be received on or
before March 8, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 2003-SW-41-AD, 2601 Meacham Blvd., Room
663, Fort Worth, Texas 76137. You may also send comments electronically
to the Rules Docket at the following address: 9-asw-adcomments@faa.gov.
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; or
at the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.
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: 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 EC130B4 helicopters
with fittings, part number (P/N) 350A25-0405-00, -01, -02, -03, -04,
and -05, installed. The DGAC advises that there have been cases of
cracks and failures of fittings.
Eurocopter France has issued Eurocopter Alert Service Bulletin No.
53A004, dated September 11, 2003, which specifies inspecting the
fittings for cracks and replacing failed fittings or those with more
than 2 cracks or 1 crack that exceeds 10 mm in length. The alert
service bulletin permits operators to stop-drill up to two cracks
provided that no crack exceeds 10 mm in length and that the fitting is
inspected every 20 flying hours, at the lastest. The DGAC classified
this alert service bulletin as mandatory and issued AD 2003-358(A),
dated October 15, 2003, to ensure the continued airworthiness of these
helicopters in France.
This helicopter model is manufactured in France and is 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 this type design that 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 registered in the United States.
Therefore, this AD is being issued to prevent failure of a forward
fitting, an excess load on the other fittings, which could cause them
to crack and break, which could result in loss of the air intake
cowling in flight, and subsequent damage or loss of control of the
helicopter, or both. This AD requires:
[sbull] For helicopters with less than 100 hours TIS, inspecting
the forward fittings no later than 110 hours TIS, then at intervals not
to exceed 110 hours TIS;
[sbull] For helicopters with 100 or more hours TIS, inspecting the
forward fittings within the next 10 hours TIS, then at intervals not to
exceed 110 hours TIS;
[sbull] If one or two forward fittings are broken or cracked,
inspecting the center and aft fittings for breaks or cracks before
further flight;
[sbull] If any fitting is broken, has a crack that exceeds 10 mm in
length, or has more than 2 cracks, replacing the fitting with an
airworthy fitting before further flight; and
[sbull] For helicopters with one or more cracked fitting with no
more than two cracks on each fitting, and each crack length is less
than or equal to 10mm, stop-drilling the cracks and inspecting the
fitting at intervals not to exceed 20 hours TIS.
The actions must be done in accordance with the alert service
bulletin described previously. The unsafe condition must be corrected
in a very short time period because loss of an air intake cowling in
flight can adversely affect the controllability or structural integrity
of the helicopter. Therefore, the previously described actions are
required, and this AD must be issued immediately. This AD is an interim
action; Eurocopter is investigating to determine the cause of the
cracked and failed fittings. Upon completion of that investigation, we
may issue another AD with terminating action for the requirements of
this AD.
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.
The FAA estimates that this AD will affect 28 helicopters and will
take approximately 1 work hour to inspect the two forward fittings. If
cracked or broken fittings are found, an additional 2 work hours will
be required to inspect the center and aft fittings, and an additional
0.5 work hour will be required to replace each cracked or broken
fitting. We estimate that the average labor rate will be $65 per work
hour. We estimate that forward fittings cost $240 each and center and
aft fittings cost $225 each. The estimated total cost of the AD for
each year will
[[Page 1522]]
be approximately $11,995, assuming that (1) The entire fleet is
inspected 5 times per year, (2) cracked forward fittings are found on
two helicopters during 2 inspections, (3) 2 forward and 2 center
fittings are replaced on one helicopter, and (4) 2 forward, 2 center,
and 2 aft fittings are replaced on the other helicopter.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications should identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available in the Rules Docket for examination by interested persons. A
report that summarizes each FAA-public contact concerned with the
substance of this AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their mailed
comments submitted in response to this rule must submit a self-
addressed, stamped postcard on which the following statement is made:
``Comments to Docket No. 2003-SW-41-AD.'' The postcard will be date
stamped and returned to the commenter.
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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, may be obtained from the Rules Docket at the
location provided under the caption ADDRESSES.
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:
2004-01-14 Eurocopter France: Amendment 39-13428. Docket No. 2003-
SW-41-AD.
Applicability: Eurocopter France Model EC130B4 helicopters with
an air intake cowling forward attachment fitting (fitting), part
number (P/N) 350A25-0405-00, -01, -02, -03, -04, and -05, installed,
certificated in any category.
Compliance: Required as indicated.
To prevent failure of a forward fitting, an excess load on the
other fittings, which could cause them to crack and break, which
could result in loss of the air intake cowling in flight, and
subsequent damage or loss of control of the helicopter, or both,
accomplish the following:
(a) Visually inspect the forward fittings for breaks or cracks
by following paragraph 2.B.1. of the Operational Procedure in
Eurocopter Alert Service Bulletin No. 53A004, dated September 11,
2003 (ASB).
(1) For helicopters with less than 100 hours time-in-service
(TIS), inspect before the helicopter reaches 110 hours TIS, unless
accomplished previously, and thereafter, at intervals not to exceed
110 hours TIS.
(2) For helicopters with 100 or more hours TIS, inspect within
10 hours TIS, unless accomplished previously, and thereafter at
intervals not to exceed 110 hours TIS.
(b) If one or two forward fittings are broken or cracked,
inspect the center and aft fittings for breaks or cracks before
further flight by following paragraph 2.B.2.b. of the ASB.
(c) Before further flight, replace any fitting that is broken or
has more than two cracks, or any fitting with a crack that exceeds
10 mm in length by following paragraph 2.B.2.c. of the Operational
Procedure in the ASB.
(d) For any cracked fitting that has no more than two cracks,
and neither crack exceeds 10 mm in length, you are not required to
replace that cracked fitting provided that you stop-drill each crack
and re-inspect that fitting at intervals not to exceed 20 hours TIS.
During a later inspection, if you discover that the fitting has
failed, another crack has developed, or a stop-drilled crack has
grown to exceed 10mm in length, replace the fitting before further
flight.
(e) 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.
(f) The inspections and replacements, if necessary, shall be
done using Eurocopter Alert Service Bulletin No. 53A004, dated
September 11, 2003. This incorporation by reference was approved by
the Director of the Federal Register 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
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
(g) This amendment becomes effective on January 26, 2004.
Note: The subject of this AD is addressed in Direction Generale
De L'Aviation Civile (France) AD 2003-358(A), dated October 15,
2003.
Issued in Fort Worth, Texas, on December 31, 2003.
Kim Smith,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 04-368 Filed 1-8-04; 8:45 am]
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