[Federal Register: November 3, 2003 (Volume 68, Number 212)]
[Rules and Regulations]               
[Page 62233-62234]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr03no03-11]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-SW-18-AD; Amendment 39-13359; AD 2003-22-11]
RIN 2120-AA64

 
Airworthiness Directives; Eurocopter France Model AS350B, B1, B2, 
B3, BA, C, D, D1, and AS355E, F, F1, F2, and N 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 (Eurocopter) Model AS350B, B1, 
B2, B3, BA, D, and AS355E helicopters, that currently requires removing 
certain serial-numbered main servocontrols before further flight. This 
amendment contains the same requirements but also requires removing 
certain other main and tail servocontrols on or before 550 hours time-
in-service (TIS) or 24 months, whichever occurs first. Also, this 
amendment adds the Eurocopter Model AS350C, D1, and AS355F, F1, F2, and 
N helicopters to the applicability. This amendment is prompted by the 
discovery of a manufacturing defect in another set of servocontrols. 
The actions specified by this AD are intended to prevent failure of a 
main or tail servocontrol in the flight control system and subsequent 
loss of control of the helicopter.

DATES: Effective December 8, 2003.

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: On December 21, 2001, the FAA issued 
Emergency AD 2001-26-53 (EAD). That EAD was published in the Federal 
Register as a final rule; request for comments on January 22, 2002, 
Docket No. 2001-SW-70-AD, Amendment 39-12605 (67 FR 2804). A proposal 
to amend 14 CFR part 39 by superseding AD 2001-26-53 for the specified 
Eurocopter model helicopters was published in the Federal Register on 
July 16, 2003 (68 FR 41968). The action proposed to retain the 
requirements in the existing AD to remove certain main servocontrols 
before further flight. The action also proposed removing certain main 
and tail servocontrols within 550 hours TIS or 24 months, whichever 
occurs first, and adding the Eurocopter Model AS350C, D1, and AS355F, 
F1, F2, and N helicopters to the applicability.
    The FAA has reviewed Eurocopter Alert Service Bulletin No. 01.00.48 
for Model AS355E, F, F1, F2, and N helicopters and No. 01.00.52 for 
Model AS350B, BA, B1, B2, B3, BB, and D helicopters, both dated May 16, 
2002, which advise replacing certain main servocontrols, before further 
flight, and certain other main and tail servocontrols within 550 hours 
or 24 months.
    The Direction General De L'Aviation Civile (DGAC), the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may exist on Eurocopter Model AS350B, BB, B1, B2, B3, BA, D, 
and AS355E, F, F1, F2, and N helicopters. The DGAC advises of the 
discovery of a manufacturing fault on a

[[Page 62234]]

set of servocontrols. The DGAC classified the Eurocopter alert service 
bulletins as mandatory and issued AD No. 2003-099(A) (for Model AS 350 
helicopters) and No. 2003-100(A) (for Model AS 355 helicopters), both 
dated March 5, 2003, to ensure the continued airworthiness of these 
helicopters.
    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.
    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.
    On July 10, 2002, the FAA issued a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs the FAA's AD system. The 
regulation now includes material that relates to altered products, 
special flight permits, and alternative methods of compliance. Because 
we have now included this material in part 39, we no longer need to 
include it in each individual AD.
    The FAA estimates that this AD will affect 627 helicopters of U.S. 
registry and will take approximately \1/2\ work hour to identify and 2 
work hours to replace each servocontrol per helicopter at an average 
labor rate of $65 per work hour. Required parts will cost approximately 
$9200 per helicopter. Based on these figures, we estimate the total 
cost impact of the AD on U.S. operators to be $5,154,130, assuming 551 
servocontrols are replaced.
    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 is contained in the Rules Docket. A copy of it may be obtained from 
the Rules Docket at the FAA, Office of the Regional Counsel, Southwest 
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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 39-12605 (67 FR 2804, 
January 22, 2002) and by adding a new airworthiness directive (AD), 
Amendment 39-13359, to read as follows:

2003-22-11 Eurocopter France: Amendment 39-13359. Docket No. 2003-
SW-18-AD. Supersedes AD 2001-26-53, Amendment 39-12605, Docket No. 
2001-SW-70-AD.

    Applicability: Model AS350B, B1, B2, B3, BA, C, D, D1, and 
AS355E, F, F1, F2, and N helicopters, certificated in any category, 
except those helicopters with TRW-SAMM main and tail servocontrols 
that have been reconditioned and identified by the letter ``V'' 
engraved on the identification plate on the right-hand side of the 
part number (P/N).
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent failure of a servocontrol in the flight control 
system and subsequent loss of control of the helicopter, accomplish 
the following:
    (a) Before further flight, remove each main servocontrol, P/N 
SC5083, serial number (S/N) 1500 through 1515, and P/N SC5084, S/N 
722 through 726.
    (b) On or before 550 hours time-in-service or 24 months, 
whichever occurs first, remove the following main or tail 
servocontrols, P/N and S/N:
    (1) P/N SC5081-1, with S/N 78, 89, 227, 240, 315, 362, 427, 451, 
452, 492, 497, 498, 506, 512, 532, 550, 556, or 561.
    (2) P/N SC5082-1, with S/N 045, 180, 194, 197, 254, or 264.
    (3) P/N SC5083, with S/N 01, 03, 05, 082, 17, 21, 40, 43M, 65M, 
77, 87, 103M, 106M, 107, 109, 128, 129, 138, 139, 144, 148, 152, 
206, 207, 218, 221, 226, 235, 239, 240, 241, 243, 254, 256, 269, 
286, 287, 290, 291, 302, 312, 321, 325, 327, 330, 331, 334, 338, 
339, 347M, 356M, 365, 371, 372, 378M, 380M, 389, 412M, 418, 423, 
428, 439, 484M, 503, 505, 525, 526, 528, 529, 573M, 587, 594M, 598, 
612, 622, 1150 through 1155, 1157, 1159 through 1169, 1180 through 
1199, 1207, 1208, 1210 through 1259, 1269, or 1291 through 1499.
    (4) P/N SC5084, with S/N 013, 025, 31, 75, 087, 87, 101M, 102, 
105, 108, 136, 160, 162, 165M, 203, 205, 205M, 209, 220, 225, 232M, 
239M, 267M, 271, 288M, 292, 300, 320, 364M, 458, 612, 627, 630, 632 
through 634, 636 through 652, 654, 656 through 660, 682 through 721, 
727 through 731, or 733 through 756.
    (5) P/N SC5071-1, with S/N 343 or 389.
    (6) P/N SC5072, with S/N 003, 35, 108, 197, 216M, 253M, 339M, 
347M, 432M, 700 through 724, 726 through 744, 763 through 768, 783 
through 789, or 820 through 883.
    (c) 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.
    (d) Special flight permits will not be issued.
    (e) This amendment becomes effective on December 8, 2003.

    Note: The subject of this AD is addressed in Direction General 
De L'Aviation Civile, France, AD Nos. 2003-099(A) and 2003-100(A), 
both dated March 5, 2003.


    Issued in Fort Worth, Texas, on October 24, 2003.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 03-27541 Filed 10-31-03; 8:45 am]

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