[Federal Register: September 26, 2005 (Volume 70, Number 185)]
[Proposed Rules]
[Page 56140-56143]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26se05-13]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-SW-10-AD]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model AS355E, F, F1,
F2, and N Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to revise an existing airworthiness
directive (AD) for the specified Eurocopter France (ECF) model
helicopters. That AD currently requires certain checks of the magnetic
chip detector plug (chip detector) and the main gearbox (MGB) oil-sight
glass, certain inspections of the lubrication pump (pump), and
replacing the MGB and the pump with an airworthy MGB and pump, if
necessary. Also, the AD requires that before an MGB or pump with any
time-in-service (TIS) can be installed, it must meet the AD
requirements. This action would retain those requirements but would
limit the applicability to one part number with certain serial-numbered
pumps or modified after a certain date. This proposal was prompted by
an investigation by the manufacturer that revealed a malfunction
occurred after modifying the pump case on certain pumps after major
overhaul and repairs.
[[Page 56141]]
The actions specified by this AD are intended to limit the
applicability to certain pumps, to detect sludge on the chip detector,
to prevent failure of the MGB pump, seizure of the MGB, loss of drive
to an engine and main rotor, and subsequent loss of control of the
helicopter.
DATES: Comments must be received by November 25, 2005.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 2003-SW-10-AD, 2601 Meacham Blvd., Room
663, Fort Worth, Texas 76137. You may also send comments electronically
to the Rules Docket at the following address: 9-asw-adcomments@faa.gov.
Comments may be inspected at the Office of the Regional Counsel between
9 a.m. and 3 p.m., Monday through Friday, except Federal holidays.
FOR FURTHER INFORMATION CONTACT: Ed Cuevas, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Safety Management Group, Fort Worth, Texas
76193-0111, telephone (817) 222-5355, fax (817) 222-5961.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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 above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their mailed
comments submitted in response to this proposal must submit a self-
addressed, stamped postcard on which the following statement is made:
``Comments to Docket No. 2003-SW-10-AD.'' The postcard will be date
stamped and returned to the commenter.
Discussion
The Direction Generale De L'Aviation Civile (DGAC), the
airworthiness authority for France, notified the FAA that an unsafe
condition may exist on the specified ECF model helicopters. The DGAC
advises that the insufficiently lubricated power transmission assembly
deteriorates until it causes the loss of the drive train for one or
even both engines.
On October 10, 2003, the FAA issued AD 2003-21-09, Docket No. 2003-
SW-10-AD, Amendment 39-13344 (68 FR 60284, October 22, 2003), which
superseded AD 2002-21-51, Docket No. 2002-SW-48-AD, Amendment 39-12982
(67 FR 77401, December 18, 2002), to require certain checks of the chip
detector and the MGB oil-sight glass, certain inspections of the pump,
and replacing the MGB and the pump with an airworthy MGB and pump, if
necessary. Also, the AD requires that before a MGB or pump with any TIS
can be installed, it must meet the AD requirements. That AD corrected
the wording from AD 2002-21-51 to specify that a check of the chip
detector should be for sludge rather than metal particles. That
condition, if not corrected, could result in failure of the MGB pump,
seizure of the MGB, loss of drive to an engine and main rotor, and
subsequent loss of control of the helicopter.
Since issuing that AD, ECF has issued Alert Service Bulletin No.
05.00.40, dated November 16, 2004 (ASB), which specifies that the
effectivity is limited to each pump, part number (P/N) 355A32-0700-01,
with a serial number (S/N) equal to or above 5731 and with a S/N below
5731, if they have been overhauled or repaired after June 1, 1995. An
investigation revealed that the malfunction is due to a modification to
the shape of the pump case. An enlarged opening of the chamber after
machining generates additional loads on the pump. The modification was
made to the one part-numbered pump with the previously specified serial
numbers; therefore, the ASB limits the effectivity to those pumps.
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. Pursuant to the
applicable bilateral agreement, the DGAC has kept the FAA informed of
the situation described above. The FAA has examined the findings of the
DGAC, reviewed all available information, and determined that AD action
is necessary for products of these type designs 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 revise AD 2003-SW-10-AD to require the same actions
as the existing AD but would limit the applicability to the specified
ECF helicopters with a pump, P/N 355A32-0700-01, with a S/N 5731 or
higher or with a S/N below 5731 if the pump has been overhauled or
repaired after June 1, 1995.
The FAA estimates that this proposed AD would affect 105
helicopters of U.S. registry assuming they all have MGB pumps with
applicable S/Ns. The proposed actions would take about:
10 minutes to check the chip detector and the MGB oil
sight glass,
4 work hours to remove the MGB and pump,
1 work hour to inspect the pump, and
4 work hours to install a serviceable MGB and pump at an
average labor rate of $65 per work hour.
Required parts would cost about $4000 for an overhauled
pump and up to $60,000 for an overhauled MGB per helicopter.
The manufacturer has represented to the FAA that the standard warranty
applies if failure occurs within the first 2 years and operating time
is less than 1000 hours. Based on these figures, we estimate the
revised total cost impact of the proposed AD on U.S. operators to be
$360,335 per year, assuming replacement of one MGB and pump on one
helicopter per year and a daily check on all helicopters for 260 days
per year.
Regulatory Findings
The regulations proposed herein 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. Therefore, it
is determined that this proposal would not have federalism implications
under Executive Order 13132.
For the reasons discussed above, I certify that this 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) if promulgated, will not have a significant economic impact,
positive or negative, on a substantial number of small entities under
the criteria of the Regulatory
[[Page 56142]]
Flexibility Act. A copy of the draft regulatory evaluation prepared for
this action is contained in the Rules Docket. A copy of it may be
obtained by contacting the Rules Docket at the location provided under
the caption ADDRESSES.
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 39-13344 (68 FR
60284, October 22, 2003), and by adding a new airworthiness directive
(AD), to read as follows:
Eurocopter France: Docket No. 2003-SW-10-AD. Revises AD 2003-21-09,
Amendment 39-13344.
Applicability: Model AS355E, F, F1, F2, and N helicopters, with
a main gear box (MGB) lubrication pump (pump), part number (P/N)
355A32-0700-01, with a serial number (S/N) 5731 or higher or with a
S/N below 5731 if the pump has been overhauled or repaired after
June 1, 1995, certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the MGB pump, seizure of the MGB, loss of
drive to an engine and main rotor, and subsequent loss of control of
the helicopter, accomplish the following:
(a) Before the first flight of each day and at intervals not to
exceed 10 hours time-in-service (TIS), check the MGB magnetic chip
detector plug (chip detector) for any sludge. Also, check for dark
oil in the MGB oil-sight glass. An owner/operator (pilot) holding at
least a private pilot certificate may perform this visual check and
must enter compliance into the aircraft maintenance records in
accordance with 14 CFR 43.11 and 91.417(a)(2)(v). ``Sludge'' is a
deposit on the chip detector that is typically dark in color and in
the form of a film or paste, as compared to metal chips or particles
normally found on a chip detector. Sludge may have both metallic or
nonmetallic properties, may consist of copper (pinion bearing),
magnesium (pump case), and steel (pinion) from the oil pump, and a
nonmetallic substance from the chemical breakdown of the oil as it
interacts with the metal.
Note 1: Eurocopter France Alert Telex No. 05.00.40R1, dated
November 27, 2002, and Alert Service Bulletin No. 05.00.40, dated
November 16, 2004, pertain to the subject of this AD.
(b) Before further flight, if any sludge is found on the chip
detector, inspect the pump.
(c) Before further flight, if the oil appears dark in color when
it is observed through the MGB oil-sight glass, take an oil sample.
If the oil taken in the sample is dark or dark purple, before
further flight, inspect the pump.
(d) While inspecting the pump, if you find any of the following,
replace the MGB and the pump with an airworthy MGB and pump before
further flight:
(1) Crank pin play,
(2) Out of round bronze bushing (A of Figure 1),
(3) Offset of the driven gear pinion,
(4) Metal chips, or
(5) Wear (C of Figure 1).
See the following Figure 1:
[[Page 56143]]
[GRAPHIC] [TIFF OMITTED] TP26SE05.021
Note 2: If wear is present in the B area only as depicted in
Figure 1, replacing the MGB and the pump is not required.
(e) Before installing a different MGB or a pump with any TIS,
accomplish the requirements of paragraph (a) of this AD.
(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 Safety Management Group, Rotorcraft Directorate, FAA,
for information about previously approved alternative methods of
compliance.
Note 3: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) AD 2002-331-071 R2, dated
November 24, 2004.
Issued in Fort Worth, Texas, on September 13, 2005.
S. Frances Cox,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 05-19148 Filed 9-23-05; 8:45 am]
BILLING CODE 4910-13-P