Airworthiness Directives; Eurocopter France Model AS332C, L, and L1 Helicopters

[Federal Register Volume 64, Number 193 (Wednesday, October 6, 1999)]
[Rules and Regulations]
[Pages 54200-54201]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-25919]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-13-AD; Amendment 39-11358; AD 99-21-13]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS332C, L, and 
L1 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to Eurocopter France Model AS332C, L, and L1 helicopters, 
that requires inspecting and replacing certain bolts that secure the 
hoist arm lower fitting. This amendment is prompted by a report of a 
failure of the bolts that secure the hoist arm lower fitting during a 
factory load test. The actions specified by this AD are intended to 
prevent failure of the bolts that secure the hoist arm lower fitting, 
separation of components from the helicopter, impact with the main or 
tail rotor, and subsequent loss of control of the helicopter.

EFFECTIVE DATE: November 10, 1999.

FOR FURTHER INFORMATION CONTACT: Shep Blackman, Aerospace Engineer,

[[Page 54201]]

FAA, Rotorcraft Directorate, Regulations Group, 2601 Meacham Blvd., 
Fort Worth, Texas 76137, telephone (817) 222-5296, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to Eurocopter France Model AS332C, L, 
and L1 helicopters was published in the Federal Register on July 7, 
1999 (64 FR 36623). That action proposed to require inspecting and 
replacing certain bolts that secure the hoist arm lower fitting.
    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 (e) and Note 2 of the AD. In paragraph 
(e), the NPRM incorrectly states that alternative methods of compliance 
(AMOC) or adjustments of the compliance time may be approved by the 
``Manager, Rotorcraft Certification Office, 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 2 of the NPRM 
states that information concerning the existence of approved AMOC may 
be obtained from the ``Rotorcraft Certification Office''; 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 4 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately 1.5 work hours per 
helicopter to inspect and replace the bolts, and that the average labor 
rate is $60 per work hour. Required parts will cost approximately $50 
for 4 bolts. Based on these figures, the total cost impact of the AD on 
U.S. operators is estimated to be $560.
    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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 FAA, Office of the Regional Counsel, 
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 
76137.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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 adding a new airworthiness directive 
to read as follows:

AD 99-21-13  Eurocopter France: Amendment 39-11358. Docket No. 99-
SW-13-AD.

    Applicability: Model AS332C, L, and L1 helicopters, that are not 
modified in accordance with modification AMS 0722955, 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: Required prior to the next use of the hoist, unless 
accomplished previously.
    To prevent failure of the bolts that secure the hoist arm lower 
fitting, separation of components from the helicopter, impact with 
the main or tail rotors, and subsequent loss of control of the 
helicopter, accomplish the following:
    (a) Remove the four bolts that secure the hoist arm lower 
fitting.
    (b ) Inspect each bolt as follows:
    (1) Measure each bolt shank from beneath the bolt head to the 
shank end;
    (2) Determine the part number (P/N) of the bolt; and
    (3) Determine what engraved marking is present on the bolt head.
    (c) Each bolt, P/N 22201BE080020L, inspected in accordance with 
paragraph (b), measuring 20 mm in length and having ``BE'' engraved 
on the bolt head may be reinstalled if otherwise airworthy.
    (d) Any bolt inspected in accordance with paragraph (b), not 
measuring 20 mm in length and having ``BC'' or letters other than 
``BE'' engraved on the bolt head must be replaced. Replace with an 
airworthy bolt, P/N 22201BE080020L, that measures 20 mm in length 
and has ``BE'' engraved on the bolt head.
    (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, 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 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (f) 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.
    (g) This amendment becomes effective on November 10, 1999.

    Note 3: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD No. 98-487-072(A), dated 
December 2, 1998.

    Issued in Fort Worth, Texas, on September 29, 1999.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-25919 Filed 10-5-99; 8:45 am]
BILLING CODE 4910-13-U

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