[Federal Register Volume 65, Number 232 (Friday, December 1, 2000)]
[Proposed Rules]
[Pages 75198-75201]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-30653]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-SW-13-AD]


Airworthiness Directives; Eurocopter France Model SA.315B, 
SA.316B, SA.316C, SE.3160, and SA.319B Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This NPRM proposes the supersedure of an existing 
airworthiness directive (AD) for Eurocopter France (ECF) Model SA.315B, 
SA.316B, SA.316C, SE.3160, and SA.319B helicopters. That AD requires 
initial and recurring inspections of the main rotor blade (blade) spar 
for cracks. This action would require initial and recurring dye 
penetrant or eddy current inspections for a cracked blade spar at 100-
hour time-in-service (TIS) intervals or 600 cycles, whichever occurs 
first, rather than the 25-hour TIS intervals currently required. This 
proposal is prompted by an accident in which a Model SA.315B helicopter 
blade failed due to fatigue cracking. The proposed actions are intended 
to prevent separation of a blade and subsequent loss of control of the 
helicopter.

DATES: Comments must be received on or before January 30, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2000-SW-13-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, Regulations Group, Fort Worth, Texas 
76193-0111, 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, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action 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 action must submit a self-
addressed,

[[Page 75199]]

stamped postcard on which the following statement is made: ``Comments 
to Docket No. 2000-SW-13-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    You 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. 2000-SW-13-AD, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas 76137.

Discussion

    On August 21, 1998, the FAA issued AD 98-10-09, Amendment 39-10725 
(63 FR 46160, August 31, 1998), to require inspecting the blade spar 
for cracks at 25-hour TIS intervals. That action was prompted by an 
accident in which a Model SA.315B helicopter blade spar failed due to 
fatigue cracking. That condition, if not corrected, could result in 
blade separation and subsequent loss of control of the helicopter.
    Since the issuance of that AD, we have determined that the initial 
and recurring inspections for a cracked blade spar should be 
accomplished by a dye penetrant or eddy current inspection at intervals 
of 100 hours TIS or 600 cycles, whichever occurs first. Eddy current 
and dye penetrant inspections are more reliable than visual inspections 
especially on the lower surface of the rotor blade where the blade's 
weight may close the crack. ECF has issued Service Bulletins (SB) SA 
315 No. 05.39 and SA 316/319 No. 05.98, both dated November 12, 1999, 
specifying a check of the main rotor blade root spar for cracks. ECF 
has also issued SB 65.137R1, dated November 17, 1993, specifying 
running a sealant bead around the spar-to-fitting junction and 
inspecting for corrosion. After investigating a main rotor blade 
failure at the first cuff-to-spar assembly bolt, ECF redefined the 
interval for crack inspections on the spar and added another criterion 
(sudden occurrence of vibrations) that makes this inspection necessary. 
A sudden occurrence of a one-per-rev vibration could indicate a cracked 
blade.
    We have identified an unsafe condition that is likely to exist or 
develop on other ECF Model SA.315B, SA.316B, SA.316C, SE.3160, and 
SA.319B helicopters of these same type designs. The proposed AD would 
supersede the current AD and redefine the recurring inspection 
interval. The proposed AD will require, within 25 hours TIS and 
thereafter at intervals not to exceed 100 hours TIS or 600 cycles, 
whichever occurs first, inspecting each blade spar for a crack, using 
dye penetrant or eddy current, and inspecting each blade cuff to ensure 
an adequate sealant bead. A ``cycle'' is any landing, regardless of 
whether the main rotor rotation is continued or stopped, or any 
completion of an external load operation; e.g. load release. If a crack 
is found, the proposed AD would require replacing the blade with an 
airworthy blade before further flight.
    The FAA estimates that 93 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 4 hours 
to inspect and 4 hours to replace a blade, if necessary, and that the 
average labor rate is $60 per work hour. Based on these figures, the 
total cost impact of the proposed AD on U.S. operators is estimated to 
be $66,960, assuming three inspections per year and no blade 
replacement.
    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.
    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:

The Proposed Amendment

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 39-10725 (63 FR 
46160), and by adding a new airworthiness directive (AD), to read as 
follows:

Eurocopter France: Docket No. 2000-SW-13-AD. Supersedes AD 98-10-09, 
Amendment 39-10725, Docket No. 98-SW-23-AD.

    Applicability: Model SA.315B, SA.316B, SA.316C, SE.3160, and 
SA.319B helicopters with a main rotor blade (blade), with any of the 
following part numbers (P/N): 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, or 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 
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 (b) 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: Required as indicated, unless accomplished 
previously.
    To prevent a blade separation and subsequent loss of control of 
the helicopter, accomplish the following:
    (a) Within 25 hours time-in-service (TIS) or before the next 
flight following the onset of any one-per-rev vibration, whichever 
occurs first, and thereafter at intervals not to exceed 100 hours 
TIS or 600 ``cycles'' (a ``cycle'' is any landing, regardless of 
whether the main rotor rotation is continued or stopped, or any 
completion of an external load operation; e.g. load release), 
whichever occurs first,
    (1) Inspect each blade spar for a crack.
    (i) Without removing the blade from the helicopter, clean each 
blade root area using ``Teepol'' or an equivalent product.
    (ii) Support the blade tip to eliminate blade droop while 
inspecting the lower blade surface.
    (iii) By either a dye penetrant or eddy current method, inspect 
each blade along the hatched area indicated in Figure 1, beginning 
on the blade lower surface, then on the flat section of the trailing 
edge (B), on the blade upper surface, and then on the flat section 
of the leading edge (A).

    Note 2: Eurocopter France Service Bulletins (SB) SA 315 No. 
05.39 and SA 316/319 No. 05.98, dated November 12, 1999, pertain to 
the subject of this AD.

    (iv) If a crack is found, replace the blade with an airworthy 
blade before further flight.
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[GRAPHIC] [TIFF OMITTED] TP01DE00.025

    (2) Ensure that there is a sealant bead (1) around the edge of 
each blade cuff. If no sealant bead exists or if a sealant bead 
shows excessive wear, before further flight, apply a sealant bead in 
accordance with paragraph 2.2 of the Accomplishment Instructions of 
Eurocopter France SB 65.137R1, dated November 17, 1993.
    (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, 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.


[[Page 75201]]


    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (c) Special flight permits will not be issued.

    Note 5: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD 1998-171-039(A)R2 and 
1998-170-056(A)R2, both dated January 12, 2000.


    Issued in Fort Worth, Texas, on November 14, 2000.
Michele M. Owsley,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-30653 Filed 11-30-00; 8:45 am]
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