AD 2001-26-55

[Federal Register Volume 67, Number 28 (Monday, February 11, 2002)]
[Rules and Regulations]
[Pages 6159-6161]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-2424]



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Federal Register / Vol. 67, No. 28 / Monday, February 11, 2002 / 
Rules and Regulations

[[Page 6159]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-74-AD; Amendment 39-12626; AD 2001-26-55]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS350B, 
AS350B1, AS350B2, AS350BA, AS350B3, AS350C, AS350D, AS350D1, AS355E, 
AS355F, AS355F1, AS355F2, and AS355N Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment 
adopting Airworthiness Directive (AD) 2001-26-55, which was sent 
previously to all known U.S. owners and operators of Eurocopter France 
(ECF) Model AS350B, AS350B1, AS350B2, AS350BA, AS350B3, AS350C, AS350D, 
AS350D1, AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters by 
individual letters. This AD requires, before further flight and 
thereafter at specified intervals, visually checking the tail rotor 
blade (blade) skin for a crack and replacing any cracked blade before 
further flight. This AD is prompted by the discovery of cracks in the 
skin of a blade. The actions specified by this AD are intended to 
prevent failure of the blade, which could result in severe vibration, 
loss of the tail rotor gearbox (TGB), and subsequent loss of control of 
the helicopter.

DATES: Effective February 26, 2002, to all persons except those persons 
to whom it was made immediately effective by Emergency AD 2001-26-55, 
issued on December 27, 2001, which contained the requirements of this 
amendment.
    Comments for inclusion in the Rules Docket must be received on or 
before April 12, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2001-SW-74-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: <a href="/cdn-cgi/l/email-protection#d8e1f5b9abaff5b9bcbbb7b5b5bdb6acab98beb9b9f6bfb7ae"><span class="__cf_email__" data-cfemail="be8793dfcdc993dfdaddd1d3d3dbd0cacdfed8dfdf90d9d1c8">[email&#160;protected]</span></a>.

FOR FURTHER INFORMATION CONTACT: Jim Grigg, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, 
Texas 76193-0110, telephone (817) 222-5490, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: On December 27, 2001, the FAA issued 
Emergency AD 2001-26-55 for ECF Model AS350B, AS350B1, AS350B2, 
AS350BA, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, 
AS355F2, and AS355N helicopters which requires, before further flight 
and thereafter at specified intervals, visually checking each blade 
skin for a crack and replacing any cracked blade before further flight. 
That action was prompted by the discovery of cracks in the skin of a 
blade. This condition, if not detected, could result in failure of a 
blade, severe vibration, loss of the TGB, and subsequent loss of 
control of the helicopter.
    The FAA has reviewed Eurocopter Alert Telex No. 05.00.40 and 
05.00.38, dated December 17, 2001, which describes procedures for 
visually checking the blade for cracks on the blade pressure face and 
blade suction face and requires replacing the blade before further 
flight if a crack is discovered.
    The Direction Generale de L'Aviation Civile (DGAC), which is the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may exist on these helicopter models. The DGAC advises of a 
report where separation of a blade trailing edge section occurred due 
to crack growth in the blade skin. The unbalance caused by the loss of 
the blade section can cause the TGB to be torn off the tailboom. The 
DGAC classified the service telex as mandatory and issued AD No. T2001-
640-089(A) and T2001-641-067(A), dated December 20, 2001, 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.
    This unsafe condition is likely to exist or develop on other ECF 
Model AS350B, AS350B1, AS350B2, AS350BA, AS350B3, AS350C, AS350D, 
AS350D1, AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters of 
the same type designs. Therefore, the FAA issued Emergency AD 2001-26-
55 to prevent failure of the blade, severe vibration, loss of the TGB, 
and subsequent loss of control of the helicopter. The AD requires, 
before further flight and thereafter before the first flight of each 
day or at intervals not to exceed 10 hours TIS, whichever occurs first, 
visually checking both sides (front and back) of each blade skin in the 
area of the trailing edge tab for a crack (see Area A of Figure 1 of 
this AD). Replacing any cracked blade is also required before further 
flight.
    The visual check required by this AD may be performed by an owner/
operator (pilot) holding at least a private pilot certificate and must 
be entered into the aircraft records showing compliance with the visual 
check requirements of paragraph (a) of this AD. However, if the owner/
operator (pilot) is in doubt about the existence of a crack, an 
inspection with a magnifying glass must be accomplished by a mechanic. 
The short compliance time involved is required because the previously 
described critical unsafe condition can adversely affect the structural 
integrity and controllability of the helicopter. Therefore, the actions 
described previously are required before further flight and at the 
specified time intervals, and this AD must be issued immediately.
    Since it was found that immediate corrective action was required, 
notice

[[Page 6160]]

and opportunity for prior public comment thereon were impracticable and 
contrary to the public interest, and good cause existed to make the AD 
effective immediately by individual letters issued on December 27, 
2001, to all known U.S. owners and operators of ECF Model AS350B, 
AS350B1, AS350B2, AS350BA, AS350B3, AS350C, AS350D, AS350D1, AS355E, 
AS355F, AS355F1, AS355F2, and AS355N helicopters. These conditions 
still exist, and the AD is hereby published in the Federal Register as 
an amendment to 14 CFR 39.13 to make it effective to all persons.
    The FAA estimates that 653 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately \1/4\ work hour 
per helicopter for each visual check, and that the average labor rate 
is $60 per work hour. Based on these figures, the total cost impact of 
the AD on U.S. operators is estimated to be $9795 to inspect the 
helicopter blade on each helicopter once.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available in the Rules Docket for examination by interested persons. A 
report that summarizes each FAA-public contact concerned with the 
substance of this AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their mailed 
comments submitted in response to this rule must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2001-SW-74-AD.'' The postcard will be date 
stamped and returned to the commenter.
    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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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, Safety.

Adoption of the Amendment

    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

    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 adding a new airworthiness directive 
to read as follows:

2001-26-55  Eurocopter France: Amendment 39-12626. Docket No. 2001-
SW-74-AD.

    Applicability: Model AS350B, AS350B1, AS350B2, AS350BA, AS350B3, 
AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, and 
AS355N helicopters, certificated in any category.

    Note 1: This AD applies to each helicopter identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise modified, altered, or repaired in the area subject to the 
requirements of this AD. For helicopters that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (f) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent failure of the tail rotor blade (blade), which could 
result in severe vibration, loss of the tail rotor gearbox, and 
subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Before further flight, and thereafter before the first 
flight of each day or at intervals not to exceed 10 hours time-in-
service (TIS), whichever occurs first, visually check both sides 
(front and back) of each blade skin in the area of the trailing edge 
tab for a crack as shown in Area A of Figure 1 of this AD.
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[GRAPHIC] [TIFF OMITTED] TR11FE02.000

    (b) The visual check required by paragraph (a) of this AD may be 
performed by an owner/operator (pilot) holding at least a private 
pilot certificate, with a maintenance record entry made in the 
aircraft records to include this AD number and paragraph (a) 
compliance date and aircraft TIS; time next due for paragraph (a) 
compliance; and name, certificate number, and type of certificate 
held by the person performing the visual check.
    (c) If in doubt about the existence of a crack in the blade 
skin, clean the area and then inspect with a 6 x  or higher 
magnifying glass.
    (d) If a crack is visible in the caulking, remove the caulking 
with 200-grit abrasive paper, taking care not to sand the skin. 
Inspect the blade skin for a crack using a 6 x  or higher magnifying 
glass.
    (e) If a crack is found in the blade skin, replace the blade 
with an airworthy blade before further flight.

    Note 2: Eurocopter Alert Telex No. 05.00.40 and 05.00.38, dated 
December 17, 2001, pertains to the subject of this AD.

    (f) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Regulations Group, Rotorcraft 
Directorate, FAA. Operators shall submit their requests through an 
FAA Principal Maintenance Inspector, who may concur or comment and 
then send it to the Manager, Regulations Group.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (g) Special flight permits will not be issued.
    (h) This amendment becomes effective on February 26, 2002, to 
all persons except those persons to whom it was made immediately 
effective by Emergency AD 2001-26-55, issued December 27, 2001, 
which contained the requirements of this amendment.

    Note 4: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France), AD No. T2001-640-089(A) and 
T2001-641-067(A), dated December 20, 2001.


    Issued in Fort Worth, Texas, on January 17, 2002.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-2424 Filed 2-8-02; 8:45 am]
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