[Federal Register Volume 64, Number 59 (Monday, March 29, 1999)]
[Rules and Regulations]
[Pages 14822-14824]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-7384]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-SW-57-AD; Amendment 39-11093; AD 99-07-08]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model SA. 315B
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) that
is applicable to Eurocopter France Model SA. 315B helicopters. This
action requires inspecting the spar skin and main rotor blade (blade)
root reinforcement strip area for bonding separation, corrosion, or a
crack, and replacing the blade, if necessary. This amendment is
prompted by the in-flight
[[Page 14823]]
failure of a blade. The actions specified in this AD are intended to
detect bonding separation, corrosion, or a crack in the area of the
blade root reinforcement strip, which could result in failure of the
blade and subsequent loss of control of the helicopter.
DATES: Effective April 13, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 13, 1999.
Comments for inclusion in the Rules Docket must be received on or
before May 28, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 98-SW-57-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
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: Richard Monschke, Aerospace Engineer,
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5116, fax (817)
222-5961.
SUPPLEMENTARY INFORMATION: The Direction Generale De L'Aviation Civile
(DGAC), which is the airworthiness authority for France, recently
notified the FAA that an unsafe condition may exist on Model SA. 315B
helicopters. The DGAC advises that, due to the failure of a blade, the
spar skin and blade root reinforcement strip area should be checked for
separations, cracks, and corrosion.
Eurocopter France has issued Eurocopter SA 315 Service Bulletin No.
05.34, Revision No. 1, dated September 28, 1998 (SB). That SB specifies
a check for bonding separation on both the spar skin and the
reinforcement strip area, and a visual inspection for cracks or
corrosion in the blade root area skin using a 3- to 7-power magnifying
glass. The DGAC classified this SB as mandatory and issued DGAC AD 98-
277-040(A), dated July 15, 1998, and 98-277-040(A)R1, dated December
16, 1998, in order to assure the continued airworthiness of these
helicopters in France. The DGAC AD and the Eurocopter SB recommend
accomplishing the initial inspection within 25 flying hours or 6
months, whichever occurs first. The FAA has determined that the initial
inspection must be accomplished before further flight to ensure public
safety.
This helicopter model is manufactured in France and is type
certificated for operation in the United States under the provisions of
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness 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. The short compliance
time involved is required because the previously described critical
unsafe condition can adversely affect the structural integrity of the
helicopter. Therefore, the initial inspections are required before
further flight, and the repetitive inspections are required at
intervals not to exceed 100 hours time-in-service (TIS) or 6 months,
whichever occurs first, and this AD must be issued immediately.
Since an unsafe condition has been identified that is likely to
exist or develop on other Eurocopter France Model SA. 315B helicopters
of the same type design registered in the United States, this AD is
being issued to detect a bonding separation, corrosion, or a crack in
the area of the blade root reinforcement strip, which could result in
failure of the blade and loss of control of the helicopter. This AD
requires inspecting each spar skin and blade root reinforcement strip
area for a bonding separation, corrosion, or a crack, and replacing the
blade if necessary. The actions are required to be accomplished in
accordance with the SB described previously.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment on this AD are impractical, and that good cause exists
for making this amendment effective in less than 30 days.
Cost Impact
The FAA estimates that 33 helicopters will be affected by this AD,
that it will take approximately 1.5 work hours to do the visual
inspection, and 16.0 hours to replace a blade, if necessary, and that
the average labor rate is $60 per work hour. Required parts will cost
approximately $40,000 per helicopter. Based on these figures, the total
cost impact of the AD on U.S. operators is estimated to be $1,354,650
to conduct one inspection, and to replace one blade per 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, both before and after the closing date for comments, 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 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. 98-SW-57-AD.'' The postcard will be date stamped and
returned to the commenter.
Regulatory Impact
The regulations adopted herein will not have substantial direct
effects 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, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
[[Page 14824]]
The FAA's Determination
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
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
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 adding a new airworthiness directive
to read as follows:
AD 99-07-08 Eurocopter France: Amendment 39-11093. Docket No. 98-
SW-57-AD.
Applicability: Model SA. 315B helicopters, with main rotor
blades, part number (P/N) 3160S11-10000--all part numbers, 3160S11-
30000--all part numbers, 3160S11-35000--all part numbers, 3160S11-
40000--all part numbers, 3160S11-45000--all part numbers, 3160S11-
50000--all part numbers, or 3160S11-55000--all part numbers,
installed, certificated in any category.
Note 1: This AD applies to each helicopter identified in the
preceding applicability provision, regardless of whether it has been
otherwise modified, altered, or repaired in the area subject to the
requirements of this AD. For helicopters that have been modified,
altered, or repaired so that the performance of the requirements of
this AD is affected, the owner/operator must request approval for an
alternative method of compliance in accordance with paragraph (c) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To detect bonding separation, corrosion, or a crack in the area
of the main rotor blade (blade) root reinforcement strip, which
could result in failure of the blade and loss of control of the
helicopter, accomplish the following:
(a) Before further flight, and thereafter at intervals not to
exceed 100 hours time-in-service (TIS) or 6 months, whichever occurs
first, inspect each blade spar skin and blade root reinforcement
strip area for bonding separation, corrosion, or a crack in
accordance with paragraphs 2.A. and 2.B. of the Accomplishment
Instructions in Eurocopter SA 315 Service Bulletin No. 05.34,
Revision No. 1, dated September 28, 1998 (SB), except that
notification to Eurocopter La Courneuve, Department E/SRPT, is not
required.
(1) For the hatched areas (15 x 50mm and 100 x 10mm) on the
upper and lower surfaces, if bonding separation is found, replace
the blade with an airworthy blade prior to further flight (refer to
Figure 1 of the SB).
(2) Bonding separation in the non-hatched area (100 x 10mm) of
the upper and lower surfaces is permissible but must be inspected
using a tapping method at intervals not to exceed 25 hours TIS in
order to monitor any propagation. If bonding separation reaches the
hatched area, the blade must be replaced with an airworthy blade
before further flight.
(b) Before further flight, and thereafter at intervals not to
exceed 100 hours TIS or 6 months, whichever occurs first, visually
inspect for a crack or corrosion on the upper and lower skin in the
100 x 100mm blade root area. If a crack or corrosion is detected,
replace the blade with an airworthy blade prior to further flight
(refer to Figure 1 of the SB).
(c) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, Rotorcraft Standards Staff,
Rotorcraft Directorate, FAA. Operators shall submit their requests
through an FAA Principal Maintenance Inspector, who may concur or
comment and then send it to the Manager, Rotorcraft Standards Staff.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Rotorcraft Standards Staff.
(d) Special flight permits will not be issued.
(e) The inspections shall be done in accordance with Eurocopter
SA 315 Service Bulletin No. 05.34, Revision No. 1, dated September
28, 1998. 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 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.
(f) This amendment becomes effective on April 13, 1999.
Note 3: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) AD 98-277-040(A), dated July
15, 1998, and AD 98-277-040(A)R1, dated December 16, 1998.
Issued in Fort Worth, Texas, on March 18, 1999.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-7384 Filed 3-26-99; 8:45 am]
BILLING CODE 4910-13-U
