

[Federal Register: December 10, 2007 (Volume 72, Number 236)]
[Rules and Regulations]               
[Page 69604-69606]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr10de07-16]                         

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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; 
Amendment 39-15290; AD 2007-25-08]
RIN 2120-AA64

 
Airworthiness Directives; Eurocopter France Model SA-365 N1, AS-
365 N2, AS-365 N3, SA-366G1, EC 155B, and EC155B1 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) 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 amendment requires 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 requires, during each required inspection or at certain 
specified intervals, ensuring the oil is at the maximum level for 
certain other model helicopters. This action also requires inspecting 
the magnetic plug for chips at specified intervals. Depending on the 
quantity of chips found, this action requires 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 requires replacing the bearing. 
This amendment 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 this 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: Effective January 14, 2008.

    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 14, 2008.

ADDRESSES: You may get the service information identified in this AD 
from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, 
Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527.
    Examining the Docket: You may examine the docket that contains this 
AD, any comments, and other information on the Internet at http://www.regulations.gov
, or at the Docket Operations office, West Building 

Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, 
DC.

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: A proposal to amend 14 CFR part 39 by 
superseding AD 2006-09-10, Amendment 39-14581 (71 FR 25930), for the 
specified ECF model helicopters was published in the Federal Register 
on June 13, 2007 (72 FR 32565). The action proposed to 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, 
the action proposed during each required inspection or at certain 
specified intervals, ensuring the oil is at the maximum level for 
certain other model helicopters. Also, proposed was inspecting the 
magnetic plug for chips at specified intervals. Depending on the 
quantity of chips found, either replacing the TGB before further flight 
or further inspecting for axial play in the T/R hub pitch change 
control spider (spider) was proposed. If axial play is found in the 
spider, before further flight, the action proposed replacing the 
bearing.
    The European Aviation Safety Agency (EASA) notified the FAA that an 
unsafe condition may exist on the specified ECF helicopters. EASA 
advises of a loss of tail rotor pitch control on a helicopter during a 
landing phase due to significant damage to the bearing of the control 
rod in the tail gear box. EASA advises that the loss of tail rotor 
pitch control can lead to the loss of yaw 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-365 N1, AS-365 N2, 
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 chips be detected at the magnetic plug of 
the TGB.
    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.
    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 adopting 
the rule

[[Page 69605]]

as proposed except we are correcting various typographical errors. The 
Federal Register citation for the superseded AD was referred to in two 
places as 85 FR 25930, and it should have been referred to as 71 FR 
25930. Additionally, the paragraph designations of the incorporated ASB 
paragraphs contained 3 small errors. These have been corrected in this 
final rule. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.
    The FAA estimates that this AD will affect 133 helicopters of U.S. 
registry, and the actions will 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
     $2,026 for required parts per helicopter.
    Based on these figures, we estimate the total cost impact of the 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 AD will not have federalism 
implications under Executive Order 13132. This AD 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.
    For the reasons discussed above, I certify that the 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 an economic evaluation of the estimated costs to comply 
with this AD. See the AD docket to examine the 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
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 removing Amendment 39-14581 (71 FR 
25930, May 3, 2006), and by adding a new airworthiness directive (AD), 
Amendment 39-15290, to read as follows:

2007-25-08 Eurocopter France: Amendment 39-15290. 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 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.
    (h) Do the inspections by following the specified portions 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 helicopters, all dated August 25, 2006, 
as applicable. 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

[[Page 69606]]

may be inspected at the FAA, Office of the Regional Counsel, 
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at NARA, call 202-
741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.

    (i) This amendment becomes effective on January 14, 2008.

    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 November 27, 2007.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E7-23605 Filed 12-7-07; 8:45 am]

BILLING CODE 4910-13-P
