[Federal Register Volume 63, Number 227 (Wednesday, November 25, 1998)]
[Rules and Regulations]
[Pages 65052-65054]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-31330]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-SW-17-AD; Amendment 39-10909; AD 98-24-23]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model SE.3160,
SA.316B, SA.316C, and SA.319B 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 SE.3160, SA.316B, SA.316C, and
SA.319B helicopters. This action requires inspecting certain horizontal
stabilizer spar tubes and replacing them if cracks are found or
repairing them if crazing, corrosion, fretting marks, or scratches are
found and are repairable. This amendment is prompted by several service
reports of spar tube corrosion and fatigue cracks discovered during
normal maintenance inspections, which could cause loss of the
horizontal stabilizer and subsequent loss of control of the helicopter.
DATES: Effective December 10, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 10, 1998.
Comments for inclusion in the Rules Docket must be received on or
before January 25, 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-17-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)
[[Page 65053]]
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: 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 Eurocopter
France Model SE.3160, SA.316B, SA.316C, and SA.319B helicopters. The
DGAC advises that fatigue cracks in certain horizontal spar tubes have
been reported originating at or near the airframe attaching fitting.
Eurocopter France has issued Eurocopter France Service Bulletin
05.84, Revision 2, dated December 19, 1997 (SB). The SB specifies
inspections of horizontal stabilizer spar tubes, part numbers (P/N)
3160.35.30.031.1 or .2, for fatigue cracks caused by corrosion or
fretting and specifies a procedure to repair them if no cracks are
present. The DGAC classified this SB as mandatory and issued AD 91-020-
049(A)R2, dated March 11, 1998, to assure 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
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.
Since an unsafe condition has been identified that is likely to
exist or develop on other Model SE.3160, SA.316B, SA.316C, and SA.319B
helicopters of the same type design registered in the United States,
this AD is being issued to prevent failure of the horizontal stabilizer
due to fatigue cracks in the horizontal stabilizer spar tubes, P/N's
3160.35.30.031.1 and .2, which could cause loss of the horizontal
stabilizer and subsequent loss of control of the helicopter. The short
compliance time involved is required because the previously described
critical unsafe condition can adversely affect the controllability of
the helicopter. Therefore, inspections of the horizontal stabilizer
spar tubes for cracks are required within 50 hours time-in-service
(TIS), and this AD must be issued immediately.
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 66 helicopters of U.S. registry will be
affected by this AD, that it will take 6 work hours per helicopter to
accomplish the actions, and that the average labor rate is $60 per work
hour. Required parts will cost approximately $1987 per helicopter.
Based on these figures, the total cost impact of this AD on U.S.
operators is estimated to be $154,902.
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-17-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:
AD 98-24-23 Eurocopter France: Amendment 39-10909. Docket No. 98-
SW-17-AD.
Applicability: Model SE.3160, SA.316B, SA.316C, and SA.319B
helicopters, certificated in any category.
Note 1: This AD applies to each helicopter identified in the
preceding applicability
[[Page 65054]]
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 (b) 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.
To prevent failure of the horizontal stabilizer due to a fatigue
crack in a spar tube, Part Number (P/N) 3160.35.30.031.1 or .2,
which could cause loss of control of the helicopter, accomplish the
following:
(a) Within 50 hours time-in-service (TIS) and thereafter at
intervals not to exceed 200 hours TIS or 12 calendar months,
whichever comes first, using a 10-power or higher magnifying glass,
visually inspect the horizontal stabilizer spar tubes, particularly
the embedded areas adjacent to the left and right attach fittings in
accordance with paragraph 1.C.1) through 5) of the Planning
Information of Eurocopter France Service Bulletin 05.84, Revision 2,
dated December 19, 1997 (SB).
(1) If the inspection reveals a crack, before further flight,
replace the spar tube with an airworthy spar tube in accordance with
paragraph 1.C.7) of the SB.
(2) If the inspection reveals any crazing (fine cracking in the
paint), before further flight, remove the paint by rubbing with 200
grit abrasive paper down to bare metal and inspect the spar tube in
accordance with paragraphs 1.C.5) and 1.C.6) a) of the SB.
(3) If corrosion pitting, fretting marks, or scratches are
found, before further flight, inspect in accordance with paragraphs
1.C.4), 1.C.5), and 1.C.6)a) and c).
(4) If any corrosion pit equals or exceeds 0.5 mm in diameter or
if a crack is found as a result of the dye penetrant inspection
specified in paragraph 1.C.6)(a) of the SB, before further flight,
replace the spar tube with an airworthy spar tube in accordance with
paragraph 1.C.7) of the SB.
(5) If pits are less than 0.5mm in diameter or corrosion,
fretting, or scratches are repairable, before further flight, repair
the spar tube in accordance with paragraph 1.C.6) and reinstall the
spar tube in accordance with paragraph 1.C.7) of the SB.
(6) If no corrosion pitting, fretting marks, scratches or
crazing are found, reinstall the spar tube in accordance with
paragraph 1.C.7) of the SB.
(b) 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.
(c) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the helicopter to a location where
the requirements of this AD can be accomplished.
(d) The inspection, replacement and repair shall be done in
accordance with Eurocopter France Service Bulletin 05.84, Revision
2, dated December 19, 1997. 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
76137; or at the Office of the Federal Register, 800 North Capitol
Street, NW., suite 700, Washington, DC.
(e) This amendment becomes effective on December 10, 1998.
Note 3: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) AD 91-020-049(A)R2 dated
March 11, 1998.
Issued in Fort Worth, Texas, on November 17, 1998.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-31330 Filed 11-24-98; 8:45 am]
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