[Federal Register Volume 68, Number 74 (Thursday, April 17, 2003)]
[Rules and Regulations]
[Pages 18856-18857]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-9013]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-52-AD; Amendment 39-13115; AD 2003-08-04]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model EC120B 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
the specified model Eurocopter France (ECF) helicopters that requires 
inspecting the attachment of the bolted assemblies of the cyclic pitch 
flight control torque tube (torque tube) for an appropriate locking 
device. If a bolted assembly is single-locked, the AD requires, if 
necessary, tightening the self-locking nuts at certain intervals and 
modifying the torque tube after a certain time. This amendment is 
prompted by the discovery that some of the attachments of the torque 
tube were fastened with a single-locking device instead of the intended 
double-locking device. The actions specified by this AD are intended to 
prevent separation of the cyclic pitch stick yokes from the torque 
tube, loss of cyclic control, and subsequent loss of control of the 
helicopter.

DATES: Effective May 22, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 22, 2003.

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, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort 
Worth, Texas 76193-0110, telephone (817) 222-5116, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to 
include an AD for the specified model ECF helicopters was published in 
the Federal Register on February 14, 2002 (67 FR 6883). That action 
proposed determining whether the attachment of the bolted assembly of 
the torque tube is a single or double-locking device; and if the bolted 
assembly is single-locked, repetitively inspecting and, if necessary, 
tightening the self-locking nuts to a specified torque. The AD also 
proposed modifying the torque tube to provide double locking for the 
attachment pins of the cyclic pitch stick yokes to the torque tube 
after a specified time interval.
    The Direction Generale De L'Aviation Civile (DGAC), the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may exist on ECF Model EC120B helicopters. The DGAC advises 
that the design fails to provide double-locking of the attachment pins 
of the cyclic pitch stick yokes to the torque tube.
    ECF has issued Alert Service Bulletin No. 67A003, dated August 2, 
2001 (ASB), which specifies inspecting single-locking devices within 50 
hours time-in-service (TIS) and modifying single-locking devices to 
make them double locking within 500 hours TIS or 24 months, whichever 
occurs first. The DGAC classified this ASB as mandatory and issued AD 
2001-373-008(A), dated August 22, 2001, to ensure the continued 
airworthiness of these helicopters in France.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comment received.
    One commenter, the manufacturer, states that the compliance time 
should be changed to 500 hours TIS or 24 months, whichever occurs 
first, in accordance with DGAC AD No. 2001-373-008(A). The commenter 
thinks the more restrictive compliance time proposed in the AD is 
unnecessary and will unnecessarily penalize U.S. operators. The 
commenter believes the initial and periodic checks required in the AD 
provide an adequate measure of safety until the modification is 
accomplished at the less restrictive compliance time. The commenter 
believes that with these checks an unsafe condition is not justified.
    The FAA agrees that the inspections in the ASB provide a temporary 
measure of safety. However, we strongly prefer terminating action in 
lieu of inspections for unsafe conditions. In this case, certain ECF 
Model EC120B helicopters were manufactured with a single locking device 
on the pins that connect the cyclic pitch stick yokes to the pitch 
torque tube. These pins must be retained by two separate locking 
devices in accordance with 14 CFR Sec.  27.607. Additionally, self-
locking nuts must incorporate a nonfriction locking device in addition 
to the self-locking device. In determining the compliance time for 
modifying the torque tube, we considered the consequences of missed 
inspections and the seriousness of this unsafe condition, possible loss 
of cyclic pitch control. The FAA has determined that, due to the 
seriousness of this unsafe condition, the torque tube must be modified 
within the next 250 hours TIS or 12 months, whichever occurs first. 
This is more than ample time for U.S. operators to install a relatively 
simple fix to terminate the inspections. Considering the safety 
implications, these compliance times do not unnecessarily penalize U.S. 
operators; therefore, the compliance time will remain as proposed.
    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.
    On July 10, 2002, the FAA issued a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs FAA's AD system. The 
regulation now includes material that relates to special flight 
permits, alternative methods of compliance, and altered products. 
However, for clarity and consistency in this final rule, we have 
retained the language of the NPRM regarding that material.
    The FAA estimates that this AD will affect 44 helicopters of U.S. 
registry, and the required actions will take approximately 5 work hours 
per helicopter to accomplish at an average labor rate of $60 per work 
hour. Required parts will cost approximately $195. Based on these 
figures, we estimate the total cost impact of the AD on U.S. operators 
to be $21,780.
    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.

[[Page 18857]]

    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

0
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

0
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]

0
2. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2003-08-04 Eurocopter France: Amendment 39-13115. Docket No. 2001-
SW-52-AD.

    Applicability: Model EC120B helicopters, serial numbers 1001 
through 1029 inclusive, 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 as indicated, unless accomplished 
previously.
    To prevent separation of the cyclic pitch stick yokes from the 
cyclic pitch flight control torque tube (torque tube), loss of 
cyclic control, and subsequent loss of control of the helicopter, 
accomplish the following:
    (a) Within 50 hours time-in-service (TIS), determine whether 
each attachment of the bolted assembly of the torque tube 
(attachment) has a single or double-locking device in accordance 
with the Accomplishment Instructions, paragraph 2.B.1., of 
Eurocopter France Alert Service Bulletin No. 67A003, dated August 2, 
2001 (ASB).
    (1) If the attachment has a double-locking device (a castellated 
self-locking nut with a cotter pin), no further action is required 
by this AD.
    (2) If the attachment has a single-locking device (a castellated 
self-locking nut without a cotter pin or a self-locking nut only), 
in accordance with the Accomplishment Instructions, paragraph 
2.B.1., of the ASB, before further flight:
    (i) Torque each nut to 0.4 to 0.5 mdaN (36 to 44 inch-lbs), and
    (ii) Apply a slippage mark on the nut and torque tube.
    (b) At intervals not to exceed 50 hours TIS, inspect the 
attachment for movement of the locking device indicated by a 
misalignment of the slippage mark.
    (1) If no movement has occurred, record the inspection.
    (2) If movement has occurred, replace, retorque, and reapply the 
slippage mark to the nut in accordance with the Accomplishment 
Instructions, paragraph 2.B.2., of the ASB.
    (c) Within 250 hours TIS or 12 months, whichever occurs first, 
modify the torque tube in accordance with the Accomplishment 
Instructions, paragraph 2.B.3., of the ASB.
    (d) Modifying the torque tube in accordance with paragraph (c) 
of this AD is terminating action for the requirements of this AD.
    (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 14 
CFR 21.197 and 21.199 to operate the helicopter to a location where 
the requirements of this AD can be accomplished.

    (g) The inspection of the attachment of the bolted assembly of 
the torque tube and modification of the torque tube shall be done in 
accordance with the Accomplishment Instructions, paragraph 2.B.1., 
2.B.2., and 2.B.3., of Eurocopter Alert Service Bulletin No. 67A003, 
dated August 2, 2001. The Director of the Federal Register approved 
this incorporation by reference 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.
    (h) This amendment becomes effective on May 22, 2003.

    Note 3: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile, (France) AD 2001-373-008(A), dated 
August 22, 2001.


    Issued in Fort Worth, Texas, on April 8, 2003.
Michele M. Owsley,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 03-9013 Filed 4-16-03; 8:45 am]
BILLING CODE 4910-13-P