Airworthiness Directives; Eurocopter France Model EC155B and B1 Helicopters

[Federal Register Volume 69, Number 146 (Friday, July 30, 2004)]
[Rules and Regulations]
[Pages 45575-45577]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-17219]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-SW-40-AD; Amendment 39-13745; AD 2004-15-11]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model EC155B and B1 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
the specified Eurocopter France (ECF) model helicopters that requires 
cleaning the auxiliary system unit (ASU) board

[[Page 45576]]

and modifying the wiring and wiring harness. If a temporary 
modification is done, the AD requires inserting a placard regarding on-
ground operation of the emergency landing gear pump (pump). Also, this 
AD revises 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 is terminating action for the requirements of this AD. This 
amendment 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 this AD are intended to prevent an 
electrical short circuit, failure of landing gear to extend, and a 
landing gear-up emergency landing.

DATES: Effective September 3, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 3, 2004.

ADDRESSES: The service information referenced in this AD may be 
obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand 
Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-
3527. This information may be examined 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.

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: A proposal to amend 14 CFR part 39 to 
include an AD for the specified model helicopters was published in the 
Federal Register on March 26, 2004 (69 FR 15744). That action proposed 
to require cleaning the ASU board and modifying the wiring and wiring 
harness. If a temporary modification is done, the action proposed to 
require inserting a placard regarding on-ground operation of the pump. 
Also, the action proposed to revise the Limitations section of the RFM 
to limit the operation of the pump. Also proposed was permanently 
modifying the wiring and wiring harness and then removing the placard 
and limitations from the RFM, which would be terminating action for the 
requirements of the AD.
    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.
    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 the 
adoption of the rule as proposed.
    The FAA estimates that this AD will affect 5 helicopters of U.S. 
registry, and modifying the electrical system will take about 11 work 
hours per helicopter at an average labor rate of $65 per work hour. 
Required parts will cost approximately $400 per helicopter. Based on 
these figures, we estimate the total cost impact of the AD on U.S. 
operators to be $5,575.
    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

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 adding a new airworthiness directive to 
read as follows:

2004-15-11 Eurocopter France: Amendment 39-13745. Docket No. 2003-
SW-40-AD.

    Applicability: Model EC155B 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:

[[Page 45577]]

    (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.
    (g) Cleaning the auxiliary system unit and modifying the wiring 
and wiring harness shall be done by following Eurocopter EC155 Alert 
Service Bulletin No. 31A005 and Alert Service Bulletin No. 31A008, 
both dated August 20, 2003, 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 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.
    (h) This amendment becomes effective on September 3, 2004.

    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 July 16, 2004.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 04-17219 Filed 7-29-04; 8:45 am]
BILLING CODE 4910-13-P

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