[Federal Register Volume 66, Number 48 (Monday, March 12, 2001)]
[Rules and Regulations]
[Pages 14301-14304]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-5164]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-SW-13-AD; Amendment 39-12132; AD 2001-04-13]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes 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 amendment requires 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 amendment is 
prompted by an accident in which an ECF Model SA.315B helicopter blade 
failed due to fatigue cracking. The actions specified by this AD are 
intended to prevent separation of a blade and subsequent loss of 
control of the helicopter.

DATES: Effective April 16, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 16, 2001.

ADDRESSES: The service information referenced in this AD may be 
obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand 
Prairie, Texas

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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: 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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 98-10-09, 
Amendment 39-10725 (63 FR 46160, August 31, 1998), which applies to ECF 
Model SA.315B, SA.316B, SA.316C, SE.3160, and SA.319B helicopters, was 
published in the Federal Register on December 1, 2000 (65 FR 75198). 
That action proposed to 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.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed but with one minor editorial change. 
Notes 4 and 5 in the proposal should have been Notes 3 and 4 
respectively, and this AD corrects that error. The FAA has determined 
that this change will neither increase the economic burden on an 
operator nor increase the scope of the AD.
    The FAA estimates that 93 helicopters of U.S. registry will be 
affected by this 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 this AD on U.S. operators is estimated to be 
$66,960, assuming three inspections per year and no blade replacement.
    The regulations adopted herein will 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 final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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 removing Amendment 39-10725 (63 FR 
46160), and by adding a new airworthiness directive (AD), Amendment 39-
12132, to read as follows:

2001-04-13  Eurocopter France: Amendment 39-12132. 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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    (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 65.137 R1, 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.

    Note 3: 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.
    (d) The modification shall be done in accordance with paragraph 
2.2 of the Accomplishment Instructions of Eurocopter France SB 
65.137 R1, dated November 17, 1993. 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; 
or at the Office of the Federal Register, 800 North Capitol Street, 
NW., suite 700, Washington, DC.
    (e) This amendment becomes effective on April 16, 2001.

    Note 4: 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 February 20, 2001.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 01-5164 Filed 3-9-01; 8:45 am]
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