[Federal Register Volume 63, Number 74 (Friday, April 17, 1998)]
[Rules and Regulations]
[Pages 19183-19184]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-10175]
[[Page 19183]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-SW-09-AD; Amendment 39-10479; AD 98-04-40]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model SA.315B,
SA.316B, SA.316C, SA.319B, and SE.3160 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This document publishes in the Federal Register an amendment
adopting Airworthiness Directive (AD) 98-04-40 which was sent
previously to all known U.S. owners and operators of Eurocopter France
Model SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 helicopters by
individual letters. This AD requires, for certain blades, inspecting
each blade spar for cracks using a dye-penetrant inspection, and
visually inspecting each blade cuff for cracks. If a crack is
discovered in either a blade spar or cuff, removal and replacement of
the blade with an airworthy blade is required prior to further flight.
This amendment is prompted by an accident in which a Model SA.315B
helicopter lost a main rotor blade (blade) just prior to take-off. The
cause of the blade failure was determined to be fatigue cracks that
originated from the outboard blade-to-cuff attachment bolt hole and
progressed through the blade spar and cuff. This condition, if not
corrected, could result in separation of a blade and subsequent loss of
control of the helicopter.
DATES: Effective May 4, 1998, to all persons except those persons to
whom it was made immediately effective by priority letter AD 98-04-40,
issued on February 12, 1998, which contained the requirements of this
amendment.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of May 4, 1998.
Comments for inclusion in the Rules Docket must be received on or
before June 16, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 98-SW-09-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
The applicable service information 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: Mr. Shep Blackman, Aerospace Engineer,
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5296, fax (817)
222-5961.
SUPPLEMENTARY INFORMATION: On February 12, 1998, the FAA issued
priority letter AD 98-04-40, applicable to Eurocopter France Model
SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 helicopters, which
requires, for blades with 400 or more hours time-in-service (TIS),
within 25 hours TIS, inspecting each blade spar for cracks using a dye-
penetrant method, and visually inspecting each blade cuff for cracks
using a 10-power or higher magnifying glass. If a crack is discovered
in either a blade spar or cuff, removal and replacement of the blade
with an airworthy blade is required prior to further flight. That
action was prompted by an accident in which a Model SA.315B helicopter
lost a main rotor blade (blade) just prior to take-off. Although the
main gearbox and the remainder of the main rotor assembly separated
from the helicopter and passed through the cockpit, there were no
fatalities. The cause of the blade failure was determined to be fatigue
cracks that originated from the outboard blade-to-cuff attachment bolt
hole and progressed through the blade spar and cuff. This condition, if
not corrected, could result in separation of a blade and subsequent
loss of control of the helicopter.
The FAA has reviewed Eurocopter France Service Telex No. 00055/
0034/98, dated February 3, 1998 (Eurocopter Service Telex: 316/319 No.
01-64 and 315 No. 01-29), which describes procedures for inspecting
each blade spar for cracks using a dye-penetrant method, and visually
inspecting each blade cuff for cracks using a 10-power or higher
magnifying glass. Additionally, the Direction Generale De L'Aviation
Civile, which is the airworthiness authority for France, has issued AD
98-088-055(A) and 98-089-038(A), both dated February 25, 1998, to
mandate these actions.
Since the unsafe condition described is likely to exist or develop
on other Eurocopter France Model SA.315B, SA.316B, SA.316C, SA.319B,
and SE.3160 helicopters of the same type design, the FAA issued
priority letter AD 98-04-40 to prevent separation of a blade and
subsequent loss of control of the helicopter. The AD requires, for
blades with 400 or more hours time-in-service (TIS), within 25 hours
TIS, inspecting each blade spar for cracks using a dye-penetrant
method, and visually inspecting each blade cuff for cracks using a 10-
power or higher magnifying glass. If a crack is discovered in either a
blade spar or cuff, removal and replacement of the blade with an
airworthy blade is required prior to further flight. The actions are
required to be accomplished in accordance with the service telex
described previously.
Since it was found that immediate corrective action was required,
notice and opportunity for prior public comment thereon were
impracticable and contrary to the public interest, and good cause
existed to make the AD effective immediately by individual letters
issued on February 12, 1998 to all known U.S. owners and operators of
Eurocopter France Model SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160
helicopters. These conditions still exist, and the AD is hereby
published in the Federal Register as an amendment to section 39.13 of
the Federal Aviation Regulations (14 CFR 39.13) to make it effective to
all persons.
The FAA estimates that 106 helicopters of U.S. Registry will be
affected by this AD, that it will take approximately 4 work hours per
helicopter to inspect each helicopter and 4 work hours to replace a
main rotor blade, and that the average labor rate is $60 per work hour.
Required parts will cost approximately $49,700 per helicopter. Based on
these figures, the total cost impact of this AD on U.S. operators is
estimated to be $5,319,080, assuming one blade replacement 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
[[Page 19184]]
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-09-AD.'' The postcard will be date stamped and
returned to the commenter.
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.
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:
98-04-40 Eurocopter France: Amendment 39-10479. Docket No. 98-SW-
09-AD.
Applicability: Model SA.315B, SA.316B, SA.316C, SA.319B, and
SE.3160 helicopters, with main rotor blades, part numbers 3160S11-
10000 all dash numbers, 3160S11-30000 all dash numbers, 3160S11-
35000 all dash numbers, 3160S11-40000 all dash numbers, 3160S11-
45000 all dash numbers, 3160S11-50000 all dash numbers, 3160S11-
55000 all dash 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
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 use the authority
provided in paragraph (d) to request approval from the FAA. This
approval may address either no action, if the current configuration
eliminates the unsafe condition, or different actions necessary to
address the unsafe condition described in this AD. Such a request
should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any helicopter from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously, for helicopters with main rotor blades (blades) having
400 or more hours time-in-service (TIS).
To prevent separation of a blade and subsequent loss of control
of the helicopter, accomplish the following:
(a) Within 25 hours TIS, inspect each blade spar for cracks
using a dye-penetrant method in accordance with paragraphs CC.1
through CC.4 of the Operational Procedures in Eurocopter France
Service Telex No. 00055/0034/98, dated February 3, 1998 (Eurocopter
Service Telex: 316/319 No. 01-64 and 315 No. 01-29).
(b) Within 25 hours TIS, visually inspect the upper and lower
surfaces of each blade cuff for cracks, especially around the
attachment pins, using a 10-power or higher magnifying glass.
(c) If a crack is found in a blade spar or cuff, remove the
blade and replace it with an airworthy blade prior to further
flight.
(d) 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.
(e) Special flight permits will not be issued.
(f) The inspection shall be done in accordance with paragraphs
CC.1 through CC.4 of the Operational Procedures in Eurocopter France
Service Telex No. 00055/0034/98, dated February 3, 1998 (Eurocopter
Service Telex: 316/319 No. 01-64 and 315 No. 01-29). 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 May 4, 1998, to all
persons except those persons to whom it was made immediately
effective by Priority Letter AD 98-04-40, issued February 12, 1998,
which contained the requirements of this amendment.
Note 3: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) AD 98-088-055(A) and 98-089-
038(A), dated February 25, 1998.
Issued in Fort Worth, Texas, on April 3, 1998.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-10175 Filed 4-16-98; 8:45 am]
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