[Federal Register Volume 69, Number 59 (Friday, March 26, 2004)]
[Proposed Rules]
[Pages 15744-15746]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-6778]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-SW-40-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model EC155B and B1 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes adopting a new airworthiness directive 
(AD) for the specified Eurocopter France (ECF) model helicopters. The 
AD would require cleaning the auxiliary system unit (ASU) board. Also, 
the AD would require modifying the wiring and wiring harness. If a 
temporary modification is done, the AD would require inserting a 
placard regarding on-ground operation of the emergency landing gear 
pump (pump). Also, the AD would revise the Limitations section of the 
Rotorcraft Flight Manual (RFM) to limit the operation of the pump. 
Permanently modifying the wiring and wiring harness and removing the 
placard and limitations from the RFM would be terminating action. This 
proposal is prompted by the report of an emergency landing with the 
landing gear retracted. The landing gear failed to extend in normal and 
emergency extension modes following failure of the ASU board 10 Alpha 
2. The actions specified by the proposed AD are intended to prevent an 
electrical short circuit, failure of landing gear to extend, and a 
landing gear-up emergency landing.

DATES: Comments must be received on or before May 25, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2003-SW-40-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]. 
Comments may be inspected at the

[[Page 15745]]

Office of the Regional Counsel between 9 a.m. and 3 p.m., Monday 
through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Jorge Castillo, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, 
Fort Worth, Texas 76193-0111, telephone (817) 222-5127, 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 will 
be considered before taking action on the proposed rule. The proposals 
contained in this document 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-40-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 Model EC 155B and B1 helicopters equipped with 
ASU board 10 Alpha 2, part number (P/N) SE07451. The DGAC advises that 
a landing gear did not extend in ``NORMAL'' and ``EMERGENCY'' extension 
modes due to a short-circuit between two components of the ASU board 10 
Alpha 2.
    ECF has issued Alert Telex No. 31A005R1, dated September 19, 2002, 
and Alert Service Bulletin (ASB) Nos. 31A005 and 31A008, both dated 
August 20, 2003. The Alert Telex and ASB No. 31A005 describe procedures 
for modifying the electrical circuit to preclude the risk of the 
landing gear not extending in the normal and emergency extension modes 
following failure of the ASU board 10 Alpha 2. ASB No. 31A008 describes 
procedures to enhance the reliability of the normal and emergency 
landing gear extension functions by separating their power supplies. 
The DGAC classified these service bulletins as mandatory and issued AD 
Nos. 2002-515(A) R1 and 2003-323(A), both dated September 3, 2003, 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. 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 registered in 
the United States. Therefore, the proposed AD would require the 
following:
     Within 15 hours time-in-service (TIS), clean the 
ASU board 10 Alpha 2.
     Within 30 days, either modify the wiring and 
wiring harness permanently or temporarily. If you elect the temporary 
modification, install a self-adhesive placard with the following text 
in white letters on a red background:
    ``CAUTION: ON GROUND OPERATION OF EMERGENCY LANDING GEAR PUMP IS 
TIME LIMITED--SEE OPERATING LIMITATIONS.''
    Also, insert the following text into the Operating Limitations 
section of the RFM:
    ``Limit the emergency landing gear pump (pump) to 10 minutes of 
continuous operation.
    When the pump is continuously operated from 1 to 5 minutes, allow 
it to cool for 15 minutes before further use.
    When the pump is continuously operated from 5 to 10 minutes, allow 
it to cool for 30 minutes before further use.''
     Within 10 months, modify the wiring and wiring 
harness.
     Remove the temporary placard, if installed, and 
the limitations from the RFM.
    The actions would be required to be accomplished following the 
service bulletins described previously. Permanently modifying the 
wiring and wiring harness and removing the temporary placard and 
operating limitations would be terminating actions for the requirements 
of this AD.
    The FAA estimates that this proposed AD would affect 5 helicopters 
of U.S. registry. The modifications of the electrical system would take 
approximately 11 work hours per helicopter to accomplish at an average 
labor rate of $65 per work hour. Required parts would cost 
approximately $400 per helicopter. Based on these figures, the total 
cost impact of the proposed AD on U.S. operators would be $5,575.
    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 Flexibility Act. A copy of the economic 
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.

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.

[[Page 15746]]

Sec.  39.13  [Amended]

    2. Section 39.13 is amended by adding a new airworthiness directive 
to read as follows:

Eurocopter France: Docket No. 2003-SW-40-AD.

    Applicability: Model EC 155B and B1 helicopters with auxiliary 
system unit (ASU) board 10 Alpha 2, part number (P/N) SE07451, 
installed, certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent an electrical short circuit, failure of landing gear 
to extend, and an emergency landing, accomplish the following:
    (a) Within 15 hours time-in-service (TIS), clean the auxiliary 
system unit (ASU) board 10 Alpha 2. Clean the ASU board by following 
the Accomplishment Instructions, paragraphs 2.B.1, and 2.B.2.a., of 
Eurocopter EC155 Alert Service Bulletin (ASB) No. 31A005, dated 
August 20, 2003 (ASB No. 31A005).
    (b) Within 30 days, modify the wiring and wiring harness 
permanently by complying with paragraph (c) of this AD or 
temporarily by following the Accomplishment Instructions, paragraphs 
2.B.1. and 2.B.2.a. through 2.B.2.d. of ASB No. 31A005. If 
temporarily modified:
    (1) Install a self-adhesive placard of the size and in the 
location depicted in Figure 4 of ASB No. 31A005 with the following 
text in white letters on a red background: ``CAUTION: ON GROUND 
OPERATION OF EMERGENCY LANDING GEAR PUMP IS TIME LIMITED--SEE 
OPERATING LIMITATIONS'' and
    (2) Revise the Operating Limitations by inserting the following 
text into the Rotorcraft Flight Manual (RFM):
    ``(i) Limit the emergency landing gear pump (pump) to 10 minutes 
of continuous operation.
    (ii) When the pump is continuously operated from 1 to 5 minutes, 
allow it to cool for 15 minutes before further use.
    (iii) When the pump is continuously operated from 5 to 10 
minutes, allow it to cool for 30 minutes before further use.''

    Note 1: Modifying the electric wiring covered by Alert Telex No. 
31A005R1, dated September 19, 2002, led to inhibiting the protective 
thermal switch of the electric pump. This resulted in the need for a 
limitation placard. The purpose of the limitation placard is to 
remind operators about the on-ground operating limitations that 
apply to the electric pump.

    (c) Within 10 months, modify the wiring and wiring harness by 
following the Accomplishment Instructions, paragraphs 2.A. and 2.B., 
of Eurocopter EC155 ASB No. 31A008, dated August 20, 2003 (ASB No. 
31A008). If you made the temporary modifications described in 
paragraph (b) of this AD, remove the placard from the helicopter and 
the limitations inserted in the RFM as a result of paragraphs (b)(1) 
and (b)(2) of this AD.
    (d) Permanently modifying the wiring and wiring harness 
following ASB No. 31A008 is terminating action for the requirements 
of this AD.
    (e) 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.
    (f) Special flight permits will not be issued.

    Note 2: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD Nos. 2002-515(A) R1 and 
2003-323(A), both dated September 3, 2003.


    Issued in Fort Worth, Texas, on March 10, 2004.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 04-6778 Filed 3-25-04; 8:45 am]
BILLING CODE 4910-13-P