Airworthiness directives: Eurocopter France,
[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]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
[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).
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.
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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
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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
-
The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
-
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:
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[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
