[Federal Register: July 16, 2003 (Volume 68, Number 136)]
[Proposed Rules]
[Page 41970-41972]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr16jy03-30]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-SW-58-AD]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model AS332C, AS332L,
AS332L1, and AS332L2 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes adopting a new airworthiness directive
(AD) for Eurocopter France (Eurocopter) Model AS332C, AS332L, AS332L1,
and AS332L2 helicopters. This proposal would require inspecting certain
main rotor blades for disbonds, which may be indicated by cracking, and
repairing or replacing each main rotor blade (MRB) as necessary. This
proposal is prompted by the discovery of disbonded leading edge
protective strips. The actions specified by this proposed AD are
intended to detect disbonding between the stainless steel protective
strip and the MRB skin, which could cause loss of the protective strip,
an out-of-balance condition, and subsequent loss of control of the
helicopter.
DATES: Comments must be received on or before September 15, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 2002-SW-58-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.
Comments may be inspected at the Office of the Regional Counsel between
9 a.m. and 3 p.m., Monday through Friday, except Federal holidays.
FOR FURTHER INFORMATION CONTACT: Jim Grigg, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Safety Management Group, Fort Worth, Texas
76193-0110, telephone (817) 222-5490, 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 will
be considered before taking action on the proposed rule. The proposals
contained in this document 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 mailed
comments submitted in response to this proposal must submit a self-
addressed, stamped postcard on which the following statement is made:
``Comments to Docket No 2002-SW-58-AD.'' The postcard will be date
stamped and returned to the commenter.
Discussion
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 AS332 C, L, and L1 helicopters.
The DGAC advises that checking each MRB to ensure the adhesion of the
glass cloth blade cap, which is located between the MRB skin and the
leading edge stainless steel protective strips, is necessary.
Eurocopter has issued AS 332 Service Bulletin 05.00.22, Revision 4,
dated April 6, 2000, for the Model AS332C, L, L1, and L2 helicopters,
which specifies checking for cracking developing spanwise along the
stainless steel leading edge over a chordwise width of 0 to 6mm aft of
the stainless steel strip on the MRB upper and lower surfaces. If
spanwise cracking is found that is greater than 30mm or if the distance
between two cracks is less than 40mm, a sound check using a tapping
method to check the bonding is specified. If disbonding is present,
measuring the depth of each disbond with a feeler gauge is specified.
If the depth of the disbond exceeds 10mm, returning the MRB to the
works for repair is specified. If no disbonding is present, or if the
disbond is less than 10mm, reconditioning the MRB by removing the
cracked caulking material and recaulking the blade is specified. The
DGAC classified this service bulletin as mandatory and issued AD 1988-
099-035(A) R5, dated June 14, 2000, to ensure the continued
airworthiness of certain 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 these type designs 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 designs registered in the United States.
Therefore, the proposed AD would require inspecting each MRB for
disbonding within 100 hours time-in-service (TIS), and repairing or
replacing each MRB as necessary. Thereafter, repetitive inspections are
[[Page 41971]]
required at different intervals, based on the MRB serial number. The
actions would be required to be accomplished in accordance with the
service bulletin described previously.
The FAA estimates that 3 helicopters of U.S. registry would be
affected by this proposed AD, that it would take approximately 2 work
hours per helicopter to inspect each MRB (8 hours per helicopter), and
that an estimated 2 MRB's per helicopter will have to be removed and
replaced with airworthy MRB's, requiring 3 work hours to remove and
replace each MRB. The average labor rate is $65 per work hour. The
estimated cost of parts is $50,000 for each blade. Based on these
figures, the total cost impact of the proposed AD on U.S. operators is
estimated to be $302,730.
The regulations proposed herein would 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 proposal would not have federalism implications
under Executive Order 13132.
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 adding a new airworthiness directive
to read as follows:
Eurocopter France: Docket No. 2002-SW-58-AD.
Applicability:
Group 1: Model AS332C, L, and L1 helicopters with main rotor
blade (MRB), part number (P/N) 332A11-0022-00 through -03; P/N
332A11-0022-04, except those incorporating MOD 0740596; P/N 332A11-
0024-00 through -05; and P/N 332A11-0025-00 through -05, installed
certificated in any category.
Group 2: Model AS332C, L, and L1 helicopters with MRB, P/N
332A11-0022-04, that incorporates MOD 0740596; P/N 332A11-0024-06
and all higher dash numbers; and P/N 332A11-0025-06 and all higher
dash numbers; and Model AS332L2 helicopters with MRB, P/N 332A11-
0040--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
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 (e) 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: Helicopters listed in ``Group 1'' of the
``Applicability'' section of this AD, comply within 100 hours time-
in-service (TIS) and thereafter at intervals not to exceed 100 hours
TIS for MRB's having a serial number listed in the following table:
126 127 131 132 134 137 139 154 156 160
162 168 171 176 196 208 209 211 219 223
224 225 226 242 253 261 272 310 327 342
377 378 379 381 383 386 391 392 394 395
398 399 404 419 422 423 424 425 426 443
455 456 458 462 482 668 744 885 909 1019
1031 1032 1033 1036 1051 1055 1061 1070 1099 1101
1106 1117 1151 1155 1157 1158 1162 1167 1168 1169
1186 1198 1201 1205 1210 1213 1242 1246 1248 1268
1332 1410 1524
For helicopters listed in ``Group 1'' of the ``Applicability''
section of this AD, with MRB's having a serial number not listed in
the previous table, comply within 100 hours TIS, and thereafter at
intervals not to exceed 250 hours TIS.
For helicopters listed in ``Group 2'' of the ``Applicability''
section of this AD, with MRB's having 400 or more hours TIS, comply
within 100 hours TIS, and thereafter at intervals not to exceed 500
hours TIS; and
For helicopters listed in ``Group 2'' of the ``Applicability''
section of this AD, with MRB's having less than 400 hours TIS,
comply prior to the MRB's accumulating 500 hours TIS, and thereafter
at intervals not to exceed 500 hours TIS.
To detect disbonding between the stainless steel protective
strip and the MRB skin, which could cause loss of the protective
strip, an out-of-balance condition, and subsequent loss of control
of the helicopter, accomplish the following:
(a) Inspect each MRB for disbonding in accordance with paragraph
2.B.1. of the Accomplishment Instructions in Eurocopter AS 332
Service Bulletin No. 05.00.22, Revision 4, dated April 6, 2000 (SB).
(b) If there is spanwise cracking which exceeds 30mm (1.18
inches) or there are 2 or more cracks with less than 40mm (1.57
inches) spacing, remove or support the MRB, remove any protective
shield, and perform a tapping test on the leading edge of the MRB.
(c) If the tapping test does not indicate a disbond, repair the
crack in accordance with paragraph 2.B.2.a) of the Accomplishment
Instructions in the SB and recaulk and apply touch-up paint in
accordance with paragraph 2.B.3. of the Accomplishment Instructions
in the SB.
(d) If the tapping test indicates a disbond, measure the depth
of the disbond in accordance with paragraph 2.B.2.b) and 2.B.2.c) of
the Accomplishment Instructions in the SB.
(1) If disbonding is less than 10mm in depth, repair the crack
in accordance with paragraph 2.B.2.a) of the Accomplishment
Instructions in the SB, and recaulk and apply touch-up paint in
accordance with paragraph 2.B.3. of the Accomplishment Instructions
in the SB.
(2) If disbonding is 10mm or greater in depth, the MRB is
unairworthy and must be replaced before further flight.
(e) 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, Safety Management Group, Rotorcraft
Directorate, FAA. Operators shall submit their requests through an
FAA Principal Maintenance Inspector, who may concur or comment and
[[Page 41972]]
then send it to the Manager, Safety Management Group.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Safety Management Group.
(f) Special flight permits may be issued in accordance with 14
CFR 21.197 and 21.199 to operate the helicopter to a location where
the requirements of this AD can be accomplished.
Note 3: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) AD 1988-099-035(A) R5, dated
June 14, 2000.
Issued in Fort Worth, Texas, on July 9, 2003.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 03-17953 Filed 7-15-03; 8:45 am]
BILLING CODE 4910-13-P