[Federal Register Volume 72, Number 113 (Wednesday, June 13, 2007)]
[Proposed Rules]
[Pages 32565-32567]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-11388]



[[Page 32565]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28448; Directorate Identifier 2006-SW-24-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA-365 N1, AS-
365N2, AS 365 N3, SA-366G1, EC 155B, and EC155B1 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 the specified Eurocopter France (ECF) model 
helicopters. That AD currently requires a onetime inspection for end 
play in the pitch control rod assembly double bearing (bearing) using 
the tail rotor (T/R) hub control plate, and before further flight, 
replacing the bearing if end play is present. This action would require 
checking the T/R gearbox (TGB) oil level before the first flight of the 
day and maintaining the oil at the maximum level for certain 
helicopters. Also, this action would require, during each required 
inspection or at certain specified intervals, ensuring the oil is at 
the maximum level for certain other model helicopters. Also, this 
action would require inspecting the magnetic plug for chips at 
specified intervals. Depending on the quantity of chips found, this 
action would require either replacing the TGB before further flight or 
further inspecting for axial play in the T/R hub pitch change control 
spider (spider). If axial play is found in the spider, before further 
flight, this AD would require replacing the bearing. This proposal is 
prompted by the finding that metal chips were not detected on the 
magnetic plug due to insufficient oil flow because the oil in the TGB 
was being maintained at the minimum level. The actions specified by the 
proposed AD are intended to detect metal chips on the magnetic plug, to 
prevent damage to the bearing resulting in end play, loss of T/R pitch 
control, and subsequent loss of control of the helicopter.

DATES: Comments must be received on or before August 13, 2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically;
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically;
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590;
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays; or
     Fax: 202-493-2251.
    You may get the service information identified in this proposed AD 
from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, 
Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527.
    You may examine the comments to this proposed AD in the AD docket 
on the Internet at http://dms.dot.gov.

FOR FURTHER INFORMATION CONTACT: Uday Garadi, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort 
Worth, Texas 76193-0110, telephone (817) 222-5123, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any written data, views, or arguments 
regarding this proposed AD. Send your comments to the address listed 
under the caption ADDRESSES. Include the docket number ``FAA-2007-
28448, Directorate Identifier 2006-SW-24-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed rulemaking. Using the search 
function of our docket Web site, you can find and read the comments to 
any of our dockets, including the name of the individual who sent or 
signed the comment. You may review the DOT's complete Privacy Act 
Statement in the Federal Register published on April 11, 2000 (65 FR 
19477-78) or you may visit http://dms.dot.gov.

Examining the Docket

    You may examine the docket that contains the proposed AD, any 
comments, and other information in person at the Docket Management 
System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Office (telephone 1-800-
647-5527) is located at the plaza level of the Department of 
Transportation NASSIF Building in Room PL-401 at 400 Seventh Street, 
SW., Washington, DC. Comments will be available in the AD docket 
shortly after the DMS receives them.

Discussion

    On April 17, 2006, the FAA issued AD 2006-09-10, Amendment 39-14581 
(85 FR 25930). That AD requires a onetime inspection for end play in 
the bearing using the T/R Hub control plate, and before further flight, 
replacing the bearing if end play is present. That action was prompted 
by an incident in which a pilot lost T/R pitch control of a helicopter 
while landing. The requirements of that AD are intended to detect 
damage to the bearing resulting in end play and prevent loss of T/R 
pitch control and subsequent loss of control of the helicopter.
    Since issuing AD 2006-09-10, ECF has issued Alert Service Bulletin 
(ASB) 05.00.54, dated August 25, 2006, for Model SA-365N1, AS-365N2, AS 
365 N3, to replace ASB 05.00.52, dated February 15, 2006. ECF has also 
issued ASB 05.37 for Model SA 366G1, dated August 25, 2006, to replace 
ASB 05.36, dated February 15, 2006. Also, ECF has issued ASB 05A015 for 
Model EC155B and EC155B1, dated August 25, 2006, to replace ASB 05A013, 
dated February 15, 2005. ASBs 05.00.52, 05.36, and 05A013 introduced a 
periodic check for absence of end play in the bearing. These ASBs were 
revised following the loss of yaw control on an AS365 MB helicopter due 
to progressive deterioration of the bearing. The metal chips resulting 
from this deterioration remained trapped in the area around the bearing 
and were not detected by the magnetic plug of the TGB. Further 
investigation and analyses revealed that the nondetection of the chips 
resulting from this deterioration was due to insufficient oil flow. 
This occurs when the oil level in the TGB is continuously maintained at 
the ``min'' level. Therefore, the ASBs specify keeping the TGB oil 
level at maximum level to ensure that any chips resulting from possible 
deterioration of the bearing are detected by the magnetic plug. Also, 
the ASBs specify checking for absence of play in the bearing should

[[Page 32566]]

chips be detected at the magnetic plug of the TGB.
    The European Aviation Safety Agency (EASA) classified these ASBs as 
mandatory and issued Emergency AD (EAD) No. 2006-0258 R1-E on August 
29, 2006. This EAD replaced EAD No. 2006-0051-E, dated February 20, 
2006, to ensure the continued airworthiness of these helicopters in 
France.
    These helicopter models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
14 CFR 21.29 and the applicable bilateral agreement. Under this 
agreement, EASA has kept the FAA informed of the situation described 
above. We have examined EASA's findings, evaluated all pertinent 
information, and determined that AD action is necessary for products of 
this type design that are certificated for operation in the United 
States.
    This previously described unsafe condition is likely to exist or 
develop on other helicopters of these same type designs. Therefore, the 
proposed AD would supersede AD 2006-09-10 to require the following:
     Before the first flight of each day for Model SA-365N1, 
AS-365N2, AS 365 N3, and SA-366G1 helicopters, check the T/R gearbox 
(TGB) oil level. An owner/operator (pilot) holding at least a private 
pilot certificate may perform the visual check of the oil level but 
must enter compliance into the aircraft maintenance records in 
accordance with 14 CFR 43.11 and 91.417(a)(2)(v). A pilot may perform 
these checks because they involve a routine check and no special tools 
are required.
     If a pilot finds the oil level is not at maximum, before 
further flight, a qualified mechanic must fill it to the maximum level.
     During each required inspection not to exceed 15 hours 
time-in-service (TIS) or 7 days, whichever occurs first, if the oil 
level is not at the maximum level, fill it to the maximum level for 
Model EC 155B and EC155B1 helicopters.
     Inspect the magnetic plug of the TGB for any chips at 
intervals not to exceed:
    [cir] 25 hours TIS for helicopters with a magnetic plug without a 
chip electrical indication in the cockpit, or
    [cir] 100 hours TIS and after any illumination of the TGB ``CHIP'' 
warning light for helicopters with a chip electrical indication in the 
cockpit.
     If you find any chips during the inspection, before 
further flight, if the quantity of chips on the magnetic plug is at or 
above the removal criteria, replace the TGB with an airworthy TGB. If 
the quantity of chips on the magnetic plug is below the removal 
criteria, inspect for axial play in the T/R hub pitch control change 
spider (spider). If there is axial play in the spider, replace the 
bearing with an airworthy bearing.
    The actions would be required by following the specified portions 
of the ASBs described previously.
    We estimate that this proposed AD would affect 133 helicopters of 
U.S. registry, and the proposed actions would require about:
     \1/2\ hour to check the oil level, fill the oil to maximum 
level, and inspect the magnetic plug for metal chips,
     \1/2\ hour to inspect for end play in the bearing;
     8 hours to remove and replace the bearing (if necessary) 
at an average labor rate of $80 per work hour; and
     $2026 for required parts per helicopter.
    Based on these figures, we estimate the total cost impact of the 
proposed AD on U.S. operators to be $365,218, assuming the bearing is 
replaced on the entire fleet after 1 oil level check, 1 magnetic plug 
inspection, and 1 end play inspection.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. Additionally, this proposed 
AD 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.
    For the reasons discussed above, I certify that the 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. 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.
    We prepared a draft economic evaluation of the estimated costs to 
comply with this proposed AD. See the DMS to examine the draft economic 
evaluation.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

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 39-14581 (85 FR 
25930, May 3, 2006), and by adding a new airworthiness directive (AD), 
to read as follows:

Eurocopter France: Docket No. FAA-2007-28448; Directorate Identifier 
2006-SW-24-AD. Supersedes AD 2006-09-10, Amendment 39-14581, Docket 
No. FAA-2006-24588, Directorate Identifier 2006-SW-07-AD.

    Applicability: Model SA-365N1, AS-365N2, AS 365 N3, SA-366G1, EC 
155B, and EC155B1 helicopters, with a tail rotor (T/R) pitch control 
rod assembly double bearing (bearing) installed, certificated in any 
category.
    Compliance: Required as indicated.
    To detect metal chips on the magnetic plug to prevent damage to 
the bearing resulting in end play, loss of T/R pitch control, and 
subsequent loss of control of the helicopter, do the following:
    (a) Before the first flight of each day for Model SA-365N1, AS-
365N2, AS 365 N3, and SA-366G1 helicopters, check the T/R gearbox 
(TGB) oil level. An owner/operator (pilot) holding at least a 
private pilot certificate may perform the visual check of the oil 
level but must enter compliance into the aircraft maintenance 
records in accordance with 14 CFR 43.11 and 91.417(a)(2)(v).
    (b) If the oil level is not at maximum during the check in 
paragraph (a) of this AD, before further flight, a qualified 
mechanic must fill it to the maximum level.
    (c) During each required inspection not to exceed 15 hours time-
in-service (TIS) or 7

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days, whichever occurs first, if the oil level is not at the maximum 
level, fill it to the maximum level for Model EC 155B and EC155B1 
helicopters.
    (d) Inspect the magnetic plug of the TGB for any chips as 
follows:
    (1) At intervals not to exceed 25 hours TIS for helicopters with 
a magnetic plug without a chip electrical indication in the cockpit, 
or
    (2) At intervals not to exceed 100 hours TIS and after any 
illumination of the TGB ``CHIP'' warning light for helicopters with 
a chip electrical indication in the cockpit.
    (e) If you find any chips during the inspection in paragraph (d) 
of this AD, before further flight, follow the Accomplishment 
Instructions, paragraph 2.B.2.b), of Eurocopter Alert Service 
Bulletin No. 05.00.54 for Model SA-365N1, AS-365N2, AS 365 N3; No. 
05A015 for Model EC 155B and EC155B1; or No. 05.37 for Model SA-
366G1 all dated August 25, 2006 (ASBs), as appropriate for your 
model helicopter.
    (1) If the quantity of chips on the magnetic plug, as referenced 
in the Operational Procedures, paragraph 2.B.2.b(1) of the ASBs is 
at or above the removal criteria, before further flight, replace the 
TGB with an airworthy TGB.
    (2) If the quantity of chips on the magnetic plug is below the 
removal criteria, as referenced in the Operational Procedure, 
paragraph 2.B.2.b(2) of the ASBs.
    (i) Inspect for axial play in the T/R hub pitch control change 
spider (spider) by following the additional steps in the Operational 
Procedure, paragraph 2.B.2.b(2) of the ASBs.
    (ii) If there is axial play in the spider, before further 
flight, replace the bearing with an airworthy bearing.
    (f) 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 Manager, Safety Management Group, ATTN: Uday Garadi, 
Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations 
and Guidance Group, Fort Worth, Texas 76193-0110, telephone (817) 
222-5123, fax (817) 222-5961.
    (g) Special flight permits will not be issued.

    Note: The subject of this AD is addressed in European Aviation 
Safety Agency Revised Emergency AD No. 2006-0258 R1-E on August 29, 
2006, which replaced AD No. 2006-0051-E, dated February 20, 2006.


    Issued in Fort Worth, Texas, on June 5, 2007.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E7-11388 Filed 6-12-07; 8:45 am]
BILLING CODE 4910-13-P