[Federal Register Volume 67, Number 135 (Monday, July 15, 2002)]
[Proposed Rules]
[Pages 46423-46425]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 02-17301]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-SW-32-AD]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model AS355N
Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes superseding an existing airworthiness
directive (AD) for Eurocopter France (ECF) Model AS355N helicopters.
The current 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 superseding
AD would retain the current requirements, except would not require
measuring the radial play but would 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 would require repairing or replacing the S-G, as
necessary. This proposal is prompted by additional cases of S-G damage
and the need for additional corrective actions. The actions specified
by this proposed 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: Comments must be received on or before September 13, 2002.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the
[[Page 46424]]
Regional Counsel, Southwest Region, Attention: Rules Docket No. 2002-
SW-32-AD, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. You
may also send comments electronically to the Rules Docket at the
following address: 9-asw-adcomments@faa.gov. Comments may be inspected
at the Office of the Federal Register between 9 a.m. and 3 p.m., Monday
through Friday, except Federal holidays.
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:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications should identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments will
be considered before taking action on the proposed rule. The proposals
contained in this document may be changed in light of the comments
received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available in the Rules Docket for
examination by interested persons. A report summarizing each FAA-public
contact concerned with the substance of this proposal will be filed in
the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their mailed
comments submitted in response to this proposal must submit a self-
addressed, stamped postcard on which the following statement is made:
``Comments to Docket No. 2002-SW-32-AD.'' The postcard will be date
stamped and returned to the commenter.
Discussion
This document proposes superseding an existing AD for ECF Model
AS355N helicopters. This action would require determining the S-G clamp
torque in accordance with the maintenance manual and the vibration
level on both engines at specified intervals. This action would also
require 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), this action would require repairing or
replacing the S-G, as necessary. Also, this action would require
inspecting the lugs, the two clamps, and the flange for a crack and
replacing any cracked part with an airworthy part before further
flight. This proposal is prompted by reports of S-G damage, cracks in
the lugs, and a report of in-flight loss of an ejector. The actions
specified by the proposed 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.
On March 6, 2000, the FAA issued AD 2000-05-15, Amendment 39-11625
(65 FR 14209), to require visually inspecting the four lugs, the
flange, and the half-clamps for cracks and the S-G shaft for radial
play. That action was prompted by reports of S-G damage, cracks in the
lugs, and a report of in-flight loss of an ejector. The requirements of
that AD are intended to prevent separation of an ejector from the
helicopter, which could result in a main or tail rotor strike and
subsequent loss of control of the helicopter.
Since the issuance of that AD, further cases of damage due to
excessive S-G vibration have resulted in modifying the technical
analysis and the precautionary measures.
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 R3,
dated November 22, 2001 that supersedes Alert Telex No. 01.00.45 R2,
dated August 24, 2000, and No. 01.00.15 R2, dated April 3, 2000, that
superseded Alert Telex No. 01.00.45, dated October 27, 1999. Alert
Telex No. 01.00.45 R3 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 R3 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.
The DGAC classified Telex Nos. 01.00.45 R2 and 01.00.45 R3 as
mandatory. The DGAC issued AD Nos. 1999-469-058(A)R1, dated August 9,
2000, and 1999-469-058(A)R2, dated January 9, 2002, to ensure the
continued airworthiness of these helicopters in France.
This helicopter model is manufactured in France and is type
certificated for operation in the United States under the provisions of
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the
applicable bilateral agreement, the DGAC has kept the FAA informed of
the situation described above. The FAA has examined the findings of the
DGAC, reviewed all available information, and determined that AD action
is necessary for products of this type design that are certificated for
operation in the United States.
This unsafe condition is likely to exist or develop on other ECF
Model AS355N helicopters of this same type design. Therefore, the
proposed AD would supersede AD 2000-05-15 to require determining the S-
G clamp torque in accordance with the maintenance manual and measuring
and recording the vibration level at specified intervals. If the
vibration level is equal to or higher than 0.5 IPS, the AD would
require repairing or replacing the S-G with an airworthy S-G, as
necessary. In addition, the AD would require inspecting the lugs, the
two clamps, and the flange for a crack, and replacing any cracked part
with an airworthy part before further flight.
The FAA estimates that this proposed AD would:
Affect 13 helicopters of U.S. registry;
Require 5.5 work hours for the inspections;
Require 5 work hours to replace the parts at an average
labor rate of $60 per work hour;
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
Result in a total cost impact of $506,584, assuming one
inspection and replacement of all parts per helicopter.
The regulations proposed herein would 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 proposal would not have federalism implications
under Executive Order 13132.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, will not have a significant economic impact,
positive or negative, on a substantial number of small entities
[[Page 46425]]
under the criteria of the Regulatory Flexibility Act. A copy of the
draft regulatory evaluation prepared for this action is contained in
the Rules Docket. A copy of it may be obtained by contacting 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.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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), to read as follows:
Eurocopter France: 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 R3, 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.
(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.
Note 3: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) AD Nos. 1999-469-058(A)R1,
dated August 9, 2000, and 1999-469-058(A)R2, dated January 9, 2002.
Issued in Fort Worth, Texas, on July 3, 2002.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-17301 Filed 7-12-02; 8:45 am]
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