[Federal Register: November 12, 2002 (Volume 67, Number 218)]
[Rules and Regulations]
[Page 68506-68508]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12no02-4]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-SW-32-AD; Amendment 39-12943; AD 2002-22-16]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model AS355N
Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD) for the specified Eurocopter France (ECF) helicopters. The
existing AD requires visually inspecting the four engine exhaust pipe
ejector (ejector) attachment lugs (lugs), the starter-generator (S-G)
attachment flange (flange) and attachment half-clamps (half-clamps) for
cracks, and the S-G shaft for radial play. This amendment will retain
the current requirements except will not require measuring the radial
play. This amendment will also require measuring each S-G engine clamp
torque and vibration level and recording the S-G vibration level on a
component history card or equivalent record. If the S-G vibration level
is equal to or higher than 0.5 inches per second (IPS), this
superseding AD requires repairing or replacing the S-G, as necessary.
This amendment is prompted by additional cases of S-G damage and the
need for additional corrective actions. The actions specified by this
AD are intended to prevent excessive S-G vibration, which could lead to
separation of an ejector, impact with the main or tail rotor, and
subsequent loss of control of the helicopter.
DATES: Effective December 17, 2002.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 17, 2002.
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,
[[Page 68507]]
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: Ed Cuevas, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Regulations Group, Fort Worth, Texas
76193-0110, telephone (817) 222-5355, fax (817) 222-5961.
SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 by
superseding AD 2000-05-15, Amendment 39-11625 (65 FR 14209) for ECF
Model AS355N helicopters was published in the Federal Register on July
15, 2002 (67 FR 46423). That action proposed determining the S-G clamp
torque and the vibration level on both engines at specified intervals.
That action also proposed recording each vibration level on the
component history card or equivalent record. If the S-G vibration level
is equal to or higher than 0.5 IPS (12.7 mm/s), that action proposed
repairing or replacing the S-G, as necessary. Also, that action
proposed retaining the requirement to visually inspect the four
ejectors, the lugs, the two half clamps, and the S-G flange for a crack
and replacing any cracked part with an airworthy part before further
flight.
The Direction Generale De L'Aviation Civile (DGAC), the
airworthiness authority for France, notified the FAA that an unsafe
condition may exist on Eurocopter France Model AS355N helicopters. The
DGAC advises of further cases of S-G deterioration, which may lead to
failure of the engine exhaust pipe lugs and loss of the ejector.
ECF has issued Eurocopter Alert Telex (Telex) No. 01.00.45 Revision
3, dated November 22, 2001 that supersedes Alert Telex No. 01.00.45
Revision 2, dated August 24, 2000, and No. 01.00.15 Revision 2, dated
April 3, 2000, that superseded Alert Telex No. 01.00.45, dated October
27, 1999. Alert Telex No. 01.00.45 Revision 3 specifies checking the S-
G clamp torque and vibration levels and recording vibration levels. If
the vibration level is equal to or above 0.5 IPS (12.7 mm/s), Telex
01.00.45 Revision 3 specifies repairing the S-G as well as conducting
additional inspections and repairs. The Telex states that ECF is
developing modifications to return to an acceptable maintenance
program.
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.
The FAA estimates that this AD will:
[sbull] Affect 13 helicopters of U.S. registry;
[sbull] Require 5.5 work hours for the inspections and 5 work hours
to replace the parts at an average labor rate of $60 per work hour;
[sbull] Cost approximately $6,346 for each S-G, $12,148 for each
exhaust pipe, $500 for each flange, and $175 for each clamp or $38,338
per helicopter; and
[sbull] Result in a total cost impact of $506,584, assuming one
inspection and replacement of all parts per helicopter.
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:
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 39-11625 (65 FR
14209, March 16, 2000), and by adding a new airworthiness directive
(AD), Amendment 39-12943, to read as follows:
2002-22-16 Eurocopter France: Amendment 39-12943. Docket No. 2002-
SW-32-AD. Supersedes AD 2000-05-15, Amendment 39-11625, Docket No.
99-SW-87-AD.
Applicability: Model AS355N helicopters, 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 excessive starter-generator (S-G) vibration, which
may lead to separation of an engine exhaust pipe ejector (ejector),
impact with the main or tail rotor, and subsequent loss of control
of the helicopter, accomplish the following:
(a) Before further flight and at or between 10 and 15 hours
time-in-service (TIS), inspect the torque on each S-G attachment
clamp (clamp). If the torque is not within tolerances provided in
the maintenance manual, adjust the torque accordingly.
(b) Measure and record on a component history card or equivalent
record the vibration level for each S-G in accordance with the
Accomplishment Instructions, paragraph 2.A.2., of Eurocopter France
(ECF) Telex No. 01.00.45 Revision 3, dated November 22, 2001
(Telex), as follows:
(1) For each S-G with less than 10 hours TIS since initial
installation, before further flight, and at or between the hours TIS
as shown in Table 1 of this AD:
Table 1.--S-G Vibration Level Measurement Intervals
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Hours TIS
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A. 10 and 15
B. 24 and 35
C. 45 and 55
D. 70 and 80
E. 100 and 110
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(2) For each S-G with 10 hours or more TIS but less than 110
hours TIS since initial installation, begin and continue the
vibration level measurements at or between the applicable hours TIS
shown in Table 1 of this AD.
[[Page 68508]]
(3) For each S-G with more than 110 hours TIS since initial
installation, measure the vibration level before further flight.
(c) After doing paragraph (b) of this AD, thereafter, at
intervals not to exceed 110 hours TIS, measure the vibration level
in accordance with paragraph 2.A.2. of the Telex.
(d) If the vibration level of an S-G is equal to or greater than
0.5 inches per second (IPS) (12.7 mm/s):
(1) Remove the S-G and repair or replace it with an airworthy S-
G.
(2) Visually inspect the four ejector attachment lugs (lugs) and
the two clamps for a crack in accordance with the Accomplishment
Instructions, paragraph 2.B.3.b.1B), of the Telex.
(3) Inspect the two half-clamps for a crack.
(4) Remove the S-G to engine attachment flange (flange). Clean
and inspect the flange for a crack in accordance with the
Accomplishment Instructions, paragraph 2.B.3.b.1D) of the Telex.
(5) If a crack is found, before further flight, repair or
replace the cracked part with an airworthy part in accordance with
the Accomplishment Instructions, paragraph 2.B.3.b.3 of the Telex,
except you are not required to report your findings to the
manufacturer.
(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) Measuring the vibration level, inspecting the lugs or
clamps, and replacing the parts shall be done in accordance with the
Accomplishment Instructions, Eurocopter France Telex No. 01.00.45
Revision 3, dated November 22, 2001. 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.
(h) This amendment becomes effective on December 17, 2002.
Note 3: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) AD Nos. 1999-469-058(A)
Revision 1, dated August 9, 2000, and 1999-469-058(A) Revision 2,
dated January 9, 2002.
Issued in Fort Worth, Texas, on October 29, 2002.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-28412 Filed 11-8-02; 8:45 am]
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