[Federal Register Volume 67, Number 218 (Tuesday, November 12, 2002)]
[Rules and Regulations]
[Pages 68506-68508]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-28412]


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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]
BILLING CODE 4910-13-P