[Federal Register Volume 65, Number 25 (Monday, February 7, 2000)]
[Rules and Regulations]
[Pages 5741-5742]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-2401]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-63-AD; Amendment 39-11550; AD 2000-02-32]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA. 315B 
Helicopters

AGENCY:  Federal Aviation Administration, DOT.

ACTION:  Final rule.

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SUMMARY:  This amendment supersedes an existing airworthiness directive 
(AD), applicable to Eurocopter France Model SA. 315B helicopters, that 
currently requires initial and repetitive visual inspections and 
modification, if necessary, of the horizontal stabilizer spar tube 
(spar tube). This amendment requires the same corrective actions as the 
existing AD and would require an additional dye-penetrant inspection of 
the half-shell attachment clamps (clamps). This amendment is prompted 
by an in-service report of fatigue cracks that initiated from corrosion 
pits. The actions specified by this 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:  Effective March 13, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 13, 2000.

ADDRESSES:  The service information referenced in this AD 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:  A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 98-12-21, 
Amendment 39-10575 (63 FR 31610), applicable to Eurocopter France Model 
SA. 315B helicopters, was published in the Federal Register on November 
8, 1999 (64 FR 60743). That action proposed to require initial and 
repetitive visual inspections and modification, if necessary, of the 
spar tube, as well as installing safety wire around each attachment 
clamp.
    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 except for two nonsubstantive changes 
that have been made to paragraph (f) and Note 3 of the AD. In paragraph 
(f), the NPRM incorrectly states that alternative methods of compliance 
(AMOC) or adjustments of the compliance time may be approved by the 
``Manager, Rotorcraft Standards Staff, Rotorcraft Directorate.'' This 
is incorrect and has been changed to state that the Manager, 
Regulations Group, Rotorcraft Directorate, is responsible for approving 
any AMOC or adjustment of the compliance time. Note 3 of the NPRM 
states that information concerning the existence of approved AMOC may 
be obtained from the ``Rotorcraft Standards Staff;'' this is also 
incorrect and has been changed to state that information may be 
obtained from the ``Regulations Group.'' The FAA has determined that 
these changes will neither increase the economic burden on any operator 
nor increase the scope of the AD.
    The FAA estimates that 28 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately 0.5 work hour per 
helicopter to accomplish the inspections; 3 work hours per helicopter 
to accomplish the modification; and 0.5 work hour per helicopter to 
inspect and fit the safety wire. The average labor rate is $60 per work 
hour. Required parts will cost approximately $1,100 per helicopter. 
Based on these figures, the total cost impact of the AD on U.S. 
operators is estimated to be $37,520.
    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:

[[Page 5742]]

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 39-10575 (63 FR 
31610), and by adding a new airworthiness directive (AD), Amendment 39-
11550, to read as follows:

AD 2000-02-32  Eurocopter France: Amendment 39-11550. Docket No. 98-
SW-63-AD. Supersedes AD 98-12-21, Amendment 39-10575, Docket No. 98-
SW-02-AD.

    Applicability: Model SA. 315B helicopters with horizontal 
stabilizers, part number (P/N) 315A35-10-000-1, 315A35-10-000-2, 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 
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 (f) 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 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, accomplish the 
following:
    (a) Before further flight:
    (1) Inspect the aircraft records and the horizontal stabilizer 
installation to determine whether Modification 072214 (installation 
of 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 Service Bulletin 
No. 55.01, Revision 4, 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 
Accomplishment Instructions 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) Within 90 calendar days and thereafter at intervals not to 
exceed 24 calendar months, visually inspect the inside of the 
horizontal spar tube in accordance with paragraph 2.A. and 2.B.1) of 
the Accomplishment Instructions 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 18 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 Accomplishment Instructions of the SB.
    (e) Within 30 calendar days, perform a one-time dye-penetrant 
inspection for cracking on the 4 attachment clamps (See No. 11 on 
Figure 3 of the SB) of the half-shells as shown in Figure 3 of the 
SB. If a crack is found in any clamp, replace the cracked clamp with 
an airworthy clamp. If no crack is found, safety wire the clamp as 
shown in Detail C in the SB using two wraps of 0.6-mm or 0.8 mm 
(.023 or .032 inch) diameter lockwire (See No. 21 on Figure 3 of the 
SB) around the clamp so that the clamp is held together in the event 
of clamp failure. After installing the safety wire, inspect the 
clamps before the first flight of each day in accordance with 
paragraph (b)(1) of this AD.
    (f) 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. 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.

    (g) 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.
    (h) The inspections and modifications shall be done in 
accordance with the Accomplishment Instructions of Eurocopter France 
Service Bulletin No. 55.01, Revision 4, dated May 4, 1998. 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.
    (i) This amendment becomes effective on March 13, 2000.

    Note 4:  The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD 96-277-037(A)R2, dated 
July 29, 1998.


    Issued in Fort Worth, Texas, on January 26, 2000.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-2401 Filed 2-4-00; 8:45 am]
BILLING CODE 4910-13-P