[Federal Register Volume 66, Number 200 (Tuesday, October 16, 2001)]
[Rules and Regulations]
[Pages 52498-52500]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-25694]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-36-AD; Amendment 39-12467; AD 2001-18-51]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA.315B, 
SA.316C, SA 3180, SA 318B, SA 318C, SA.319B, SE.3160, and SA.316B 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment 
adopting Airworthiness Directive (AD) 2001-18-51, which was sent 
previously to all known U.S. owners and operators of Eurocopter France 
(ECF) Model SA.315B, SA.316C, SA 3180, SA 318B, SA 318C, SA.319B, 
SE.3160, and SA.316B helicopters by individual letters. This AD 
requires, within 10 hours time-in-service (TIS), inspecting the 
magnetic drain plug and the main gear box (MGB) filter for a rust-
colored deposit, inspecting the MGB to determine the angular 
displacement on the MGB output flange, and periodically examining oil 
samples. If a rust-colored deposit is found on the drain plug or 
filter, if the oil is rust-colored, or if the angular displacement is 1 
millimeter (0.039 inch) or more, this AD requires replacing the MGB 
with an airworthy MGB before further flight. Repairing or overhauling 
the gearbox, or re-identifying certain gearboxes that have already been 
appropriately overhauled, is terminating action for the requirements of 
this AD. This AD is prompted by an accident of an ECF Model SA.315B 
helicopter that lost power to the tail rotor. The loss of power to the 
tail rotor was due to wear of the splines of the output bevel drive 
pinion in the MGB. The actions specified by this AD are intended to 
prevent a loose splined coupling, spline wear, loss of power to the 
tail rotor, and subsequent loss of control of the helicopter.

DATES: Effective October 31, 2001, to all persons except those persons 
to whom it was made immediately effective by Emergency AD 2001-18-51, 
issued on August 31, 2001, which contained the requirements of this 
amendment.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 31, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before December 17, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2001-SW-36-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].
    The applicable service information 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, Rotorcraft Standards Staff, Fort Worth, 
Texas 76193-0110, telephone (817) 222-5123, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: On August 31, 2001, the FAA issued Emergency 
AD 2001-18-51, for ECF Model SA.315B, SA.316C, SA 3180, SA 318B, SA 
318C, SA.319B, SE.3160, and SA.316B helicopters, which requires, within 
10 hours TIS, inspecting the magnetic drain plug and the MGB filter for 
a rust-colored deposit, inspecting the MGB to determine the angular 
displacement on the MGB output flange, and periodically examining oil 
samples. If a rust-colored deposit is found on the drain plug or 
filter, if the oil is rust-colored, or if the angular displacement is 1 
millimeter (0.039 inch) or more, the AD requires replacing the MGB with 
an airworthy MGB before further flight. Repairing or overhauling the 
gearbox, or re-identifying certain gearboxes that have already been 
appropriately overhauled, is terminating action for the requirements of 
the AD. That action was prompted by an accident of an ECF Model SA.315B 
helicopter that lost power to the tail rotor. The loss of power to the 
tail rotor was due to wear of the splines of the output bevel drive 
pinion in the MGB. An overhaul and repair shop used an unauthorized 
sealant that led to spline wear. This condition, if not corrected, 
could result in a loose splined coupling, spline wear, loss of power to 
the tail rotor, and subsequent loss of control of the helicopter.
    Eurocopter has issued Alert Service Bulletin Nos. 05.40 and 05.99, 
both dated August 7, 2001, which specify checking the wear rate of the 
lower pinion-to-MGB vertical shaft bevel gear housing coupling splines. 
The Direction Generale de L'Aviation Civile (DGAC), which is the 
airworthiness authority for France, classified these service bulletins 
as mandatory and issued ADs T2001-366-059(A), T2001-367-062(A), and 
T2001-368-045(A), all dated August 13, 2001, to ensure the continued 
airworthiness of these helicopters in France.
    Since the unsafe condition described is likely to exist or develop 
on other ECF Model SA.315B, SA.316C, SA 3180, SA 318B, SA 318C, 
SA.319B, SE.3160, and SA.316B helicopters of the same type designs, the 
FAA issued Emergency AD 2001-18-51 to prevent a loose splined coupling, 
spline wear, loss of power to the tail rotor, and subsequent loss of 
control of the helicopter. The AD requires the following at specified 
hours TIS:
     If appropriate, re-identify the MGB. Appropriately re-
identifying certain MGBs is terminating action for the requirements of 
this AD.
     Inspect the magnetic drain plug and the MGB filter for a 
rust-colored deposit. Inspect the MGB to determine the angular 
displacement on the MGB output flange.
     If a rust-colored deposit is found or if the angular 
displacement is 1 millimeter (0.039 inch) or more, replace the MGB with 
an airworthy MGB before further flight.

[[Page 52499]]

     Take an oil sample and drain the MGB. If the oil is rust-
colored, replace the MGB with an airworthy MGB before further flight. 
If the oil is not rust-colored, take a sample for future comparison.
     At each oil change, take a sample and compare it to the 
previous sample. If the oil is rust-colored, replace the MGB with an 
airworthy MGB before further flight. If the color is unchanged, store 
the last sample for future comparison.

    The actions must be accomplished in accordance with the alert 
service bulletins described previously. The short compliance time 
involved is required because the previously described critical unsafe 
condition can adversely affect the structural integrity and 
controllability of the helicopter. Therefore, the actions described 
previously are required within 10 hours TIS, and this AD must be issued 
immediately.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment thereon were 
impracticable and contrary to the public interest, and good cause 
existed to make the AD effective immediately by individual letters 
issued on August 31, 2001, to all known U.S. owners and operators of 
ECF Model SA.315B, SA.316C, SA 3180, SA 318B, SA 318C, SA.319B, 
SE.3160, and SA.316B helicopters. These conditions still exist, and the 
AD is hereby published in the Federal Register as an amendment to 14 
CFR 39.13 to make it effective to all persons.
    The FAA estimates that 73 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately 2.5 work hours per 
helicopter to accomplish the required actions, and the average labor 
rate is $60 per work hour. Required parts will cost approximately $15 
per helicopter. Based on these figures, the total cost impact of the AD 
on U.S. operators is estimated to be $12,045.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available in the Rules Docket for examination by interested persons. A 
report that summarizes each FAA-public contact concerned with the 
substance of this AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their mailed 
comments submitted in response to this rule must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2001-SW-36-AD.'' The postcard will be date 
stamped and returned to the commenter.
    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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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 adding a new airworthiness directive 
to read as follows:

2001-18-51  Eurocopter France: Amendment 39-12467. Docket No. 2001-
SW-36-AD.

    Applicability: Model SA.315B, SA.316C, SA 3180, SA 318B, SA 
318C, SA.319B, SE.3160, and SA.316B main gearbox assembly (MGB), 
part number 319A62-00-000-1, 319A62-00-000-2, 319A62-00-000-3, 
319A62-00-000-4, with one of the following serial-numbered MGBs 
installed, certificated in any category:

10007, 3-10204, 3-10206, 3-10272, 3-10335, 3-10377, 3-10382, 3-
10424, 3-10434, 3-10437, 3-10441, 3-10490, 3-10574, 3-10603, 3-
10640, 3-10663, 3-10676, 3-10709, 3-10710, 3-10712, 3-10731, 3-
10751, 3-10753, 3-10766, 3-10804, 3-10814, 3-10853, 3-10902, 3-
10927, 3-10943, 3-10950, 3-10951, 3-10988, 3-10989, 3-110, 3-11008, 
3-11026, 3-11104, 3-11124, 3-11190, 3-11210, 3-11232, 3-11238, 3-
11301, 3-11376, 3-11427, 3-11511, 3-11537, 3-11565, 3-11571, 3-
11583, 3-11607, 3-11608, 3-11662, 3-11691, 3-11694, 3-11698, 3-
11735, 3-11775, 3-2115, 3-2174, 3-2217, 3-2218, 3-2263, 3-2267, 3-
2279, 3-2286, 3-2300, 3-2303, 3-2305, 3-2307, 3-2322, 3-2334, 3-
2345, 3-2346, 3-2347, 3-2348, 3-2352, 3-2353, 3-2354, 3-2355, 3-
2372, 3-2373, 3-2374, 3-2391, 3-2399, 3-2400, 3-2410, 3-2411, 3-
2413, 3-2414, 3-2415, 3-2424, 3-2442, 3-2445, 3-2470, 3-2472, 3-
2481, 3-2484, 3-2495, 3-2500, 3-2503, 3-2515, 3-2545, 3-2549, 3-
2555, 3-2573, 3-2574, 3-2582, 3-2584, 3-2589, 3-2591, 3-2594, 3-
2596, 3-2597, 3-2616, 3-2688, 3-2736, 3-2741, 3-2751, 3-2764, 3-
2769, 3-2782, 3-2783, 3-2818, 3-2820, 3-2850, 3-2852, 3-2871, 3-
2891, 3-2896, 3-2917, 3-2927, 3-2934, 3-2943, 3-2954, 3-2955, 3-
2960, 3-3001, 3-3090, 3-3094, 3-3110, 3-3131, 3-3137, 3-3144, 3-
3166, 3-3179, 3-3195, 3-3217, 3-3218, 3-3221, 3-3232, 3-3251, 3-
3265, 3-3279, 3-3283, 3-3286, 3-3299, 3-3317, 3-3318, 3-3319, 3-
3329, 3-3355, 3-3358, 3-3372, 3-3375, 3-3633, 3-431, 3-536.
M-2013, M-2061, M-2072, M-2079, M-2139, M-2144, M-2145.
NT-3378, NT-3380, NT-3404, NT-3423, NT-3429, NT-3443, NT-3447, NT-
3449, NT-3467, NT-3474, NT-3490, NT-3502, NT-3509, NT-3539, NT-3552, 
NT-3560, NT-3586, NT-3590, NT-3620, NT-3653, NT-3671, NT-3676, NT-
3722, NT-3724, NT-3729.


[[Page 52500]]


    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 (f) 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 a loose splined coupling, spline wear, loss of power 
to the tail rotor, and subsequent loss of control of the helicopter, 
accomplish the following:
    (a) Within 10 hours time-in-service (TIS), re-identify the MGB, 
if appropriate, in accordance with the Accomplishment Instructions, 
paragraph 2.C., of Eurocopter France Alert Service Bulletin No. 
05.40 or 05.99, dated August 7, 2001 (ASB), as applicable. Re-
identifying a MGB in accordance with the Accomplishment 
Instructions, paragraph 2.C., of the applicable ASB is terminating 
action for the requirements of this AD.
    (b) Within 10 hours TIS, accomplish the following procedures in 
accordance with the specified paragraphs of the Accomplishment 
Instructions of the ASB, except this AD does not require you to 
return the MGB to PILATUS.
    (1) Inspect the magnetic drain plug and the MGB oil filter for a 
rust-colored deposit in accordance with paragraph 2.B.1.a) of the 
applicable ASB. If a rust-colored deposit is found, replace the MGB 
with an airworthy MGB before further flight.
    (2) Inspect the angular displacement on the MGB output flange in 
accordance with paragraph 2.B.1.b) of the applicable ASB. If the 
angular displacement is 1 millimeter (0.039 inch) or more, replace 
the MGB with an airworthy MGB before further flight.
    (3) Take an oil sample and drain the MGB in accordance with 
paragraph 2.B.1.c) of the applicable ASB. If the oil is rust-
colored, replace the MGB with an airworthy MGB before further 
flight. If the oil is not rust-colored, store the sample.
    (c) Between 40 and 50 hours TIS, accomplish the requirements of 
paragraph (b)(2) of this AD and take an oil sample from the MGB. If 
the oil is rust-colored, replace the MGB with an airworthy MGB 
before further flight. If the oil is not rust-colored, store the 
last sample.
    (d) At intervals not to exceed 10 hours TIS, accomplish the 
requirements of paragraph (b)(1) of this AD.
    (e) At each oil change, accomplish the requirements of 
paragraphs (b) and (c) of this AD, and compare the oil sample to the 
previous sample. If the oil is rust-colored, replace the MGB with an 
airworthy MGB before further flight. If the color is unchanged, 
store the last sample for future comparison.
    (f) 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, Rotorcraft 
Directorate.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (g) 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.
    (h) The modifications and inspections shall be done in 
accordance with the Accomplishment Instructions, paragraphs 
2.B.1.a), 2.B.1.b), 2.B.1.c), and 2.C, of Eurocopter France Alert 
Service Bulletin No. 05.40 or 05.99, as applicable. Both service 
bulletins are dated August 7, 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.
    (i) This amendment becomes effective on October 31, 2001, to all 
persons except those persons to whom it was made immediately 
effective by Emergency AD 2001-18-51, issued August 31, 2001, which 
contained the requirements of this amendment.

    Note 3: The subject of this AD is addressed in Direction 
Generale de L'Aviation Civile (France) ADs T2001-366-059(A), T2001-
367-062(A), and T2001-368-045(A), all dated August 13, 2001.


    Issued in Fort Worth, Texas, on October 3, 2001.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 01-25694 Filed 10-15-01; 8:45 am]
BILLING CODE 4910-13-U