[Federal Register: April 17, 2003 (Volume 68, Number 74)]
[Rules and Regulations]
[Page 18856-18857]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr17ap03-6]
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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]
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