[Federal Register Volume 67, Number 135 (Monday, July 15, 2002)]
[Proposed Rules]
[Pages 46423-46425]
From the Federal Register Online via the Government Publishing 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: [email protected]. 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]
BILLING CODE 4910-13-P