[Federal Register Volume 64, Number 222 (Thursday, November 18, 1999)]
[Proposed Rules]
[Pages 62988-62990]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-30147]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 64, No. 222 / Thursday, November 18, 1999 /
Proposed Rules
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-SW-65-AD]
Airworthiness Directives; Eurocopter France Model SE 3130, SA
3180, SE 313B, SA 318B, and SA 318C Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the supersedure of an existing
airworthiness directive (AD), applicable to Eurocopter France Model SE
3130, SA 3180, SE 313B, SA 318B, and SA 318C helicopters. The existing
AD currently requires visual inspections and modification, if
necessary, of the horizontal stabilizer spar tube (spar tube). This
action would require the same corrective actions as the existing AD but
would also require visually inspecting the four half-shell attachment
clamps for cracks and fitting a safety wire around the attachment
clamps. This proposal is prompted by an in-service report of fatigue
cracks that initiated from corrosion pits. The actions specified by the
proposed AD are intended to prevent fatigue failure of the spar tube,
separation of the horizontal stabilizer and impact with the main or
tail rotor, and subsequent loss of control of the helicopter.
DATES: Comments must be received on or before January 18, 2000.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 98-SW-65-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137. Comments may be inspected at this location
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal
holidays.
The service information referenced in the proposed rule 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:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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 above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 98-SW-65-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 98-SW-65-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
Discussion
On June 2, 1998, the FAA issued AD 98-12-20, Amendment 39-10574 (63
FR 31350, June 9, 1998), to require initial and repetitive visual
inspections and modification, if necessary, of the spar tube. That
action was prompted by an in-service report of fatigue cracks that
initiated from corrosion pits. The requirements of that AD are intended
to prevent fatigue failure of the spar tube, separation and impact of
the horizontal stabilizer with the main or tail rotor, and subsequent
loss of control of the helicopter.
Since the issuance of that AD, Eurocopter France has issued
Eurocopter France SA3130/3180 Service Bulletin No. 55.10, Revision 3,
dated May 4, 1998, which specifies a visual inspection of the spar
tube, inspection and modification of the stabilizer supports,
modification of the stabilizer, visually inspecting the four attachment
clamps for cracking, and fitting a lockwire around the four attachment
clamps.
The Direction Generale De L'Aviation Civile (DGAC), which is the
airworthiness authority for France, has notified the FAA that an unsafe
condition may exist on Eurocopter France Model SE 3130, SA 3180, SE
313B, SA 318B, and SA 318C helicopters. The DGAC advises that improving
the horizontal stabilizer fatigue strength is necessary in these model
helicopters and has issued AD 96-278-054(A)R2, dated July 29, 1998.
These helicopter models are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 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.
[[Page 62989]]
Since an unsafe condition has been identified that is likely to
exist or develop on other Eurocopter France Model SE 3130, SA 3180, SE
313B, SA 318B, and SA 318C helicopters of the same type design, this
proposed AD would supersede AD 98-12-20 to require the same actions
required by that AD but would also require visually inspecting the four
half-shell attachment clamps for cracks, replacing any cracked
attachment clamp, and fitting a safety wire around the attachment
clamps.
Cost Impact
The FAA estimates that 14 helicopters of U.S. registry would be
affected by this proposed AD. It would take approximately 0.5 work hour
per helicopter to accomplish the inspection, 3 work hours per
helicopter to accomplish the modification, and 1 work hour to
accomplish the attachment clamp inspection and to install the safety
wire. The average labor rate is $60 per work hour. Required parts would
cost approximately $1,100 per helicopter. Based on these figures, the
total cost impact of the proposed AD on U.S. operators is estimated to
be $19,180.
Regulatory Impact
The regulations proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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 removing Amendment 39-10574 (63 FR
31350, June 9, 1998), and by adding a new airworthiness directive (AD),
to read as follows:
Eurocopter France: Docket No. 98-SW-65-AD. Supersedes AD 98-12-20,
Amendment 39-10574, Docket No. 98-SW-03-AD.
Applicability: Model SE 3130, SA 3180, SE 313B, SA 318B, and SA
318C helicopters with horizontal stabilizer, part number (P/N) 3130-
35-60-000, 3130-35-60-000-1, 3130-35-60-000-2, 3130-35-60-000-3,
3130-35-60-000-4 or higher 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 (g) 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 fatigue failure of the horizontal stabilizer spar
tube (spar tube), separation of the horizontal stabilizer and impact
with the main or tail rotor, and subsequent loss of control of the
helicopter, accomplish the following:
(a) Before further flight:
(1) Inspect the aircraft records and the horizontal stabilizer
to determine whether Modification 072214 (installing the spar tube
without play) or Modification 072215 (adding two half-shells on the
spar) has been accomplished.
(2) If Modification 072214 has not been installed, comply with
paragraphs 2.A., 2.B.1), 2.B.2)a), and 2.B.2)b) of the
Accomplishment Instructions of Eurocopter France SA3130/3180 Service
Bulletin No. 55.10, Revision 3, dated May 4, 1998 (SB). If the fit
and dimensions of the components specified in paragraph 2.B.2)a)
exceed the tolerances in the applicable structural repair manual,
replace with airworthy parts.
(3) If Modification 072215 has not been installed, first comply
with paragraphs 2.A., 2.B.1), and 2.B.3), and then comply with
paragraph 2.B.2)c) of the Accomplishment Instructions of the SB.
Note 2: Modification kit P/N 315A-07-0221571 contains the
necessary materials to accomplish this modification.
(b) Before the first flight of each day:
(1) Visually inspect the installation of the half-shells, the
horizontal stabilizer supports, and the horizontal stabilizer for
corrosion or cracks. Repair any corroded parts in accordance with
the applicable maintenance manual. Replace any cracked components
with airworthy parts before further flight.
(2) Confirm that there is no play in the horizontal stabilizer
supports by lightly shaking the horizontal stabilizer. If play is
detected, comply with paragraphs 2.A. and 2.B.2)a) of the SB. If the
fit and dimensions of the components specified in paragraph 2.B.2)a)
exceed the tolerances in the applicable structural repair manual,
replace with airworthy parts before further flight.
(c) At intervals not to exceed 400 hours time-in-service (TIS)
or four calendar months, whichever occurs first, inspect and
lubricate the spar tube attachment bolts.
(d) For stabilizers, P/N 3130-35-60-000, 3130-35-60-000-1, 3130-
35-60-000-2, or 3130-35-60-000-3, within 90 days and thereafter at
intervals not to exceed 18 calendar months, visually inspect the
inside of the horizontal spar tube in accordance with paragraph 2.A.
and 2.B.1) of the SB.
(1) If corrosion is found inside the tube, other than in the
half-shell area, replace the tube with an airworthy tube within the
next 500 hours TIS or 24 calendar months, whichever occurs first.
(2) If corrosion is found inside the tube in the half-shell
area, apply a protective treatment as described in paragraph
2.B.1)b) of the SB.
(e) For stabilizers, P/N 3130-35-60-000-4 or higher dash
numbers, accomplish the following:
(1) At or before the next major inspection, 3,200 hours total
TIS, or 144 calendar months total TIS, whichever occurs first, and
thereafter at each major inspection, visually inspect the inside of
the horizontal spar tube in accordance with paragraph 2.A. and
2.B.1) of the SB.
(2) If corrosion is found inside the tube, other than in the
half-shell area, replace the tube with an airworthy tube within the
next 500 hours TIS or 18 calendar months, whichever occurs first. If
corrosion is found inside the tube in the half-shell area, apply a
protective treatment as described in paragraph 2.B.1)b) of the SB.
(f) Within 30 calendar days, visually inspect the four
attachment clamps of the half-shells and install a safety wire
around the four attachment clamps in accordance with paragraph
2.B.2)d) of the SB. If any attachment clamp is found cracked,
replace it with an airworthy attachment clamp and
[[Page 62990]]
install a safety wire around the replacement attachment clamp before
further flight.
(g) 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, Regulations Group, 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, Regulations Group.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Regulations Group.
(h) 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.
Note 4: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) AD 96-278-054(A)R2, dated
July 29, 1998.
Issued in Fort Worth, Texas, on November 10, 1999.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-30147 Filed 11-17-99; 8:45 am]
BILLING CODE 4910-13-P