[Federal Register Volume 68, Number 136 (Wednesday, July 16, 2003)]
[Proposed Rules]
[Pages 41970-41972]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-17953]


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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: [email protected]. 
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