[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