[Federal Register Volume 61, Number 61 (Thursday, March 28, 1996)]
[Rules and Regulations]
[Pages 13655-13659]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-7494]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-SW-04-AD; Amendment 39-9552; AD 96-07-03]
Airworthiness Directives; Societe Nationale Industrielle
Aerospatiale and Eurocopter France Model AS 350B, BA, B1, B2, and D,
and Model AS 355E, F, F1, F2, and N Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to Societe Nationale Industrielle Aerospatiale and
Eurocopter France (Eurocopter France) Model AS 350B, BA, B1, B2, and D,
and Model AS 355E, F, F1, F2, and N helicopters, without an autopilot
installed, that requires a visual inspection to determine whether the
cyclic pitch change control rod (rod) end fittings were safetied, and
removal
[[Page 13656]]
and replacement of the rod if the rod end fittings were not safetied.
This amendment is prompted by a manufacturer's report that some of the
rod end fittings had not been safetied at the factory. The actions
specified by this AD are intended to prevent loss of tightening torque
on the adjustment nuts of the rod, shifting of the neutral point of the
cyclic stick, reduction in the amount of available movement of the
cyclic stick in the roll axis, and subsequent reduction in the
controllability of the helicopter.
EFFECTIVE DATE: Effective May 2, 1996.
FOR FURTHER INFORMATION CONTACT: Mr. 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) to include an airworthiness
directive (AD) that is applicable to Eurocopter France Model AS 350B,
BA, B1, B2, and D, and Model AS 355E, F, F1, F2, and N helicopters,
without an autopilot installed, was published in the Federal Register
on November 1, 1995 (60 FR 55491). That action proposed to require a
visual inspection to confirm that the rod end fittings are safetied,
and removal and replacement of the rod, if necessary.
Eurocopter France has issued Eurocopter Service Bulletin No. 01.38,
dated June 26, 1994, for the Model AS 355 series helicopters, and
Eurocopter Service Bulletin No. 01.42, dated June 28, 1994, for the
Model AS 350 series helicopters, which specifies a visual inspection to
determine whether the rod end fittings have been safetied;
reinstallation of the forward lower fairing if the rod end fittings
have been safetied, and removal and replacement of the rod with an
airworthy rod and reinstallation of the forward lower fairing if the
rod end fittings have not been safetied. The Direction Generale De
L'Aviation Civile, which is the airworthiness authority for France,
classified this service bulletin as mandatory and issued AD 94-179-
051(B) and AD 94-180-069(B), both dated August 3, 1994, in order to
assure the continued airworthiness of these helicopters in France.
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. However,
a note has been inserted at the end of paragraph (c) to alert the
reader that a Eurocopter Service Bulletin has been issued that pertains
to the requirements of this AD. The FAA has determined that air safety
and the public interest require the adoption of the rule with the noted
change.
The FAA estimates that 498 helicopters of U.S. registry will be
affected by this AD, that it will take approximately one-fourth of a
work hour per helicopter to inspect the rod end fittings, and 1 work
hour to remove and reinstall the rod, if necessary, and that the
average labor rate is $60 per work hour. Required parts will be
provided by the manufacturer. Based on these figures, the total cost
impact of the AD on U.S. operators is estimated to be $37,350.
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 location provided under the caption
ADDRESSES.
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 USC 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 96-07-03 Societe Nationale Industrielle Aerospatiale and
Eurocopter France: Amendment 39-9552. Docket No. 95-SW-04-AD.
Applicability: Model AS 350B, BA, B1, B2, and D, and Model AS
355E, F, F1, F2, and N helicopters, with cyclic pitch change control
rod, part number (P/N) 704A34-113-279, installed, and without an
autopilot 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
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 use the authority
provided in paragraph (d) to request approval from the FAA. This
approval may address either no action, if the current configuration
eliminates the unsafe condition, or different actions necessary to
address the unsafe condition described in this AD. Such a request
should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any helicopter from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent loss of tightening torque on the adjustment nuts of the
cyclic pitch change control rod, shifting of the neutral position of
the cyclic stick, reduction in the amount of available movement of the
cyclic stick in the roll axis, and subsequent reduction in the
controllability of the helicopter, accomplish the following:
(a) Within 100 hours time-in-service (TIS) after the effective date
of this AD, remove the forward lower fairing and visually inspect the
cyclic pitch change control rod (rod), P/N 704A34-113-279, to determine
whether the end fittings have been safetied (see Figure 1, Detail 1,
tabs bent around the adjustment nut).
(b) If the visual inspection indicates that the rod end fittings
have been safetied, reinstall the forward lower fairing.
(c) If the visual inspection indicates that the rod end fittings
have not been safetied (see Figure 1, Detail 2, tabs not bent around
the adjustment nut), accomplish the following in accordance with the
applicable maintenance manual:
(1) Immobilize the cyclic control.
(2) Remove the rod and replace it with an airworthy rod on which
the rod end fittings have been safetied.
(3) Reinstall the forward lower fairing.
[[Page 13657]]
(4) Verify proper operation of the cyclic control.
Note 2: Eurocopter Service Bulletin No. 01.38, dated June 26,
1994, for the Model AS 355 series helicopters, and Eurocopter
Service Bulletin No. 01.42, dated June 28, 1994, for the Model AS
350 series helicopters, pertain to this subject.
(d) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be used
when approved by the Manager, Rotorcraft Standards Staff, FAA,
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, Rotorcraft Standards Staff.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Rotorcraft Standards Staff.
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(e) 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.
(f) This amendment becomes effective on May 2, 1996.
Issued in Fort Worth, Texas, on March 20, 1996.
Daniel P. Salvano,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 96-7494 Filed 3-27-96; 8:45 am]
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