[Federal Register Volume 69, Number 30 (Friday, February 13, 2004)]
[Rules and Regulations]
[Pages 7113-7114]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-2782]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-SW-45-AD; Amendment 39-13471; AD 2004-03-27]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS332C, L, and 
L1 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
the specified Eurocopter France (Eurocopter) model helicopters that 
requires inspecting the bevel gear for a crack using a borescope. This 
amendment is prompted by a crack that was detected on a bevel gear 
during a main gearbox teardown inspection. The actions specified by 
this AD are intended to prevent failure of the bevel gear, loss of 
torque to the main rotor system, and subsequent loss of control of the 
helicopter.

DATES: Effective March 19, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 19, 2004.

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, 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: Uday Garadi, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Safety Management Group, Fort Worth, Texas 
76193-0110, telephone (817) 222-5123, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an AD that is 
applicable to Eurocopter Model AS332C, L, and L1 helicopters was 
published in the Federal Register on December 31, 2002 (67 FR 79893). 
That action proposed to require inspecting the bevel gear for cracks 
using a borescope within 50 hours TIS, and thereafter at intervals not 
to exceed 150 hours TIS, for bevel gears with more than 6,600 hours 
TIS. If a crack was found in the bevel gear, it was proposed that 
replacing the bevel gear would be required. However, before the final 
rule was published, we discovered that certain part-numbered bevel 
gears were omitted from the applicability and one was incorrectly 
stated in that previous proposal. Also, the manufacturer revised the 
service information to introduce the new inspection interval of 1,000 
cycles for helicopter operations involving a torque application 
frequency of more than 4 cycles per hour for helicopters that conduct 
external load operations involving more frequent torque applications. 
Additionally, we inadvertently included Model AS332C1 helicopters in 
the ``Applicability'' section of the proposal--those model helicopters 
are not on the U.S. Registry. Finally, the DGAC issued a revised AD for 
helicopters operated in France. Therefore, we reopened the comment 
period by publishing a supplemental notice of proposed rulemaking on 
September 18, 2003 (68 FR 54686). That action:
    <bullet<ls-thn-eq> Corrected the basic bevel gear part number (P/N) 
stated in the ``Applicability'' of the proposal to state ``332A32-2181-
00'';
    <bullet<ls-thn-eq> Added bevel gear P/Ns 332A32-2181-01 and -08 to 
the ``Applicability'';
    <bullet<ls-thn-eq> Deleted the Model AS332C1 helicopters from the 
``Applicability'';
    <bullet<ls-thn-eq> Incorporated the latest Eurocopter Alert Telex 
and referenced the latest DGAC AD;
    <bullet<ls-thn-eq> Proposed requiring the repetitive inspection at 
intervals not to exceed 150 hours TIS or 1,000 torque cycles, whichever 
occurs first; and
    <bullet<ls-thn-eq> Excluded from the ``Applicability'' any main 
gearbox (regardless of the P/N of the main reduction gear module or 
bevel gear) overhauled after December 31, 2002, and any P/N inspected 
in accordance with AS332 letter to Repair Stations No. 183 or repaired 
in accordance with Repair Sheet (F.R.) 332A32-2181-ZA or 331A32-3110-
ZA.
    The Direction Generale De L'Aviation Civile (DGAC), the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may exist on Eurocopter Model AS332C, C1, L, and L1 
helicopters. The DGAC advises that borescope inspections of the bevel 
gear are necessary to detect cracks.
    Eurocopter has issued Alert Telex No. 05.00.58 R2, dated February 
3, 2003, which indicates that as a result of metal particles found on 
the chip detector of the main gearbox sump on a helicopter, further 
investigation has revealed a longitudinal crack that grows lengthwise 
in the shaft, up to the

[[Page 7114]]

combiner gear, in the bevel gear where the ring retains the pinion toe 
bearing. The alert telex specifies inspecting the bevel gear for cracks 
using a borescope, pending the result of the investigation into the 
cause of the fatigue crack initiation currently being conducted in 
France. The DGAC classified this alert telex as mandatory and issued AD 
2002-424-081(A) R2, dated March 19, 2003, to ensure 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. 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 affect 4 helicopters of U.S. 
registry, and the required actions will take approximately 4 work hours 
for the inspections and 16 work hours to replace the bevel gear, if 
necessary, at an average labor rate of $65 per work hour. Required 
parts will cost approximately $31,372. Based on these figures, we 
estimate the total cost impact of the AD on U.S. operators to be 
$130,688, assuming that upon the first inspection a crack is detected 
and the bevel gear will need to be replaced.
    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

0
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]

0
2. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2002-SW-45-AD Eurocopter France: Amendment 39-13471. Docket No. 
2002-SW-45-AD.

    Applicability: Model AS332C, L, and L1 helicopters, with main 
gearbox bevel gear (bevel gear), part numbers (P/N) 332A32-2027-00 
or 332A32-2026-00, containing bevel gears, P/N 332A32-2181-00, -01, 
-02, -03, or -04, or 331A32-3110-07, -08, -09, or -19, installed, 
certificated in any category. This AD does not apply to:
    <bullet<ls-thn-eq> Main gearboxes that were overhauled after 
December 31, 2002;
    <bullet<ls-thn-eq> Parts inspected in accordance with AS332 
letter to Repair Stations No. 183; or
    <bullet<ls-thn-eq> Parts repaired in accordance with Repair 
Sheet (F.R.) 332A32-2181-ZA or 331A32-3110-ZA.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect a bevel gear crack and prevent failure of the bevel 
gear, loss of torque to the main rotor system, and subsequent loss 
of control of the helicopter, accomplish the following:
    (a) For bevel gears that have more than 6,600 hours time-in-
service (TIS), within 50 hours TIS and thereafter at intervals not 
to exceed 150 hours TIS, or at intervals not to exceed 1,000 
frequent torque variation cycles, whichever occurs first, inspect 
for a crack using a borescope in accordance with the Operational 
Procedure, paragraph 2.B.1. and 2.B.2. of Eurocopter Telex No. 
05.00.58 R2, dated February 3, 2003. A frequent torque variation 
cycle is each landing or external load operation beginning at the 
point when there are 4 or more landings, or 4 or more external load 
operations, or any combination of 4 or more landings and external 
load operations in any 60 minute time period, and ending when any 
combination of landings and external load operations is less than 4 
in any 60 minute time period.
    (b) If a crack is found in the bevel gear, before further 
flight, replace the bevel gear with an airworthy bevel gear.
    (c) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Safety Management Group, Rotorcraft Directorate, FAA, 
for information about previously approved alternative methods of 
compliance.
    (d) The inspection and replacement, if necessary, shall be done 
in accordance with Eurocopter Telex No. 05.00.58 R2, dated February 
3, 2003. The Director of the Federal Register approved this 
incorporation by reference 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.
    (e) This amendment becomes effective on March 19, 2004.

    Note: The subject of this AD is addressed in Direction Generale 
De L'Aviation Civile (France) AD 2002-424-081(A) R2, dated March 19, 
2003.


    Issued in Fort Worth, Texas, on January 30, 2004.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 04-2782 Filed 2-12-04; 8:45 am]
BILLING CODE 4910-13-P