[Federal Register Volume 64, Number 59 (Monday, March 29, 1999)]
[Rules and Regulations]
[Pages 14822-14824]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-7384]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-57-AD; Amendment 39-11093; AD 99-07-08]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA. 315B 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to Eurocopter France Model SA. 315B helicopters. This 
action requires inspecting the spar skin and main rotor blade (blade) 
root reinforcement strip area for bonding separation, corrosion, or a 
crack, and replacing the blade, if necessary. This amendment is 
prompted by the in-flight

[[Page 14823]]

failure of a blade. The actions specified in this AD are intended to 
detect bonding separation, corrosion, or a crack in the area of the 
blade root reinforcement strip, which could result in failure of the 
blade and subsequent loss of control of the helicopter.

DATES: Effective April 13, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 13, 1999.
    Comments for inclusion in the Rules Docket must be received on or 
before May 28, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 98-SW-57-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.
    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 Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Richard Monschke, Aerospace Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham 
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5116, fax (817) 
222-5961.

SUPPLEMENTARY INFORMATION: The Direction Generale De L'Aviation Civile 
(DGAC), which is the airworthiness authority for France, recently 
notified the FAA that an unsafe condition may exist on Model SA. 315B 
helicopters. The DGAC advises that, due to the failure of a blade, the 
spar skin and blade root reinforcement strip area should be checked for 
separations, cracks, and corrosion.
    Eurocopter France has issued Eurocopter SA 315 Service Bulletin No. 
05.34, Revision No. 1, dated September 28, 1998 (SB). That SB specifies 
a check for bonding separation on both the spar skin and the 
reinforcement strip area, and a visual inspection for cracks or 
corrosion in the blade root area skin using a 3- to 7-power magnifying 
glass. The DGAC classified this SB as mandatory and issued DGAC AD 98-
277-040(A), dated July 15, 1998, and 98-277-040(A)R1, dated December 
16, 1998, in order to assure the continued airworthiness of these 
helicopters in France. The DGAC AD and the Eurocopter SB recommend 
accomplishing the initial inspection within 25 flying hours or 6 
months, whichever occurs first. The FAA has determined that the initial 
inspection must be accomplished before further flight to ensure public 
safety.
    This helicopter model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the 
applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness 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 this type design that are 
certificated for operation in the United States. The short compliance 
time involved is required because the previously described critical 
unsafe condition can adversely affect the structural integrity of the 
helicopter. Therefore, the initial inspections are required before 
further flight, and the repetitive inspections are required at 
intervals not to exceed 100 hours time-in-service (TIS) or 6 months, 
whichever occurs first, and this AD must be issued immediately.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other Eurocopter France Model SA. 315B helicopters 
of the same type design registered in the United States, this AD is 
being issued to detect a bonding separation, corrosion, or a crack in 
the area of the blade root reinforcement strip, which could result in 
failure of the blade and loss of control of the helicopter. This AD 
requires inspecting each spar skin and blade root reinforcement strip 
area for a bonding separation, corrosion, or a crack, and replacing the 
blade if necessary. The actions are required to be accomplished in 
accordance with the SB described previously.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment on this AD are impractical, and that good cause exists 
for making this amendment effective in less than 30 days.

Cost Impact

    The FAA estimates that 33 helicopters will be affected by this AD, 
that it will take approximately 1.5 work hours to do the visual 
inspection, and 16.0 hours to replace a blade, if necessary, and that 
the average labor rate is $60 per work hour. Required parts will cost 
approximately $40,000 per helicopter. Based on these figures, the total 
cost impact of the AD on U.S. operators is estimated to be $1,354,650 
to conduct one inspection, and to replace one blade per helicopter.

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, both before and after the closing date for comments, 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 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. 98-SW-57-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.

[[Page 14824]]

The FAA's Determination

    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, Incorporation by 
reference, 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:

AD 99-07-08  Eurocopter France: Amendment 39-11093. Docket No. 98-
SW-57-AD.

    Applicability: Model SA. 315B helicopters, with main rotor 
blades, part number (P/N) 3160S11-10000--all part numbers, 3160S11-
30000--all part numbers, 3160S11-35000--all part numbers, 3160S11-
40000--all part numbers, 3160S11-45000--all part numbers, 3160S11-
50000--all part numbers, or 3160S11-55000--all part numbers, 
installed, 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 (c) 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 detect bonding separation, corrosion, or a crack in the area 
of the main rotor blade (blade) root reinforcement strip, which 
could result in failure of the blade and loss of control of the 
helicopter, accomplish the following:
    (a) Before further flight, and thereafter at intervals not to 
exceed 100 hours time-in-service (TIS) or 6 months, whichever occurs 
first, inspect each blade spar skin and blade root reinforcement 
strip area for bonding separation, corrosion, or a crack in 
accordance with paragraphs 2.A. and 2.B. of the Accomplishment 
Instructions in Eurocopter SA 315 Service Bulletin No. 05.34, 
Revision No. 1, dated September 28, 1998 (SB), except that 
notification to Eurocopter La Courneuve, Department E/SRPT, is not 
required.
    (1) For the hatched areas (15  x  50mm and 100  x  10mm) on the 
upper and lower surfaces, if bonding separation is found, replace 
the blade with an airworthy blade prior to further flight (refer to 
Figure 1 of the SB).
    (2) Bonding separation in the non-hatched area (100  x  10mm) of 
the upper and lower surfaces is permissible but must be inspected 
using a tapping method at intervals not to exceed 25 hours TIS in 
order to monitor any propagation. If bonding separation reaches the 
hatched area, the blade must be replaced with an airworthy blade 
before further flight.
    (b) Before further flight, and thereafter at intervals not to 
exceed 100 hours TIS or 6 months, whichever occurs first, visually 
inspect for a crack or corrosion on the upper and lower skin in the 
100  x  100mm blade root area. If a crack or corrosion is detected, 
replace the blade with an airworthy blade prior to further flight 
(refer to Figure 1 of the SB).
    (c) 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, Rotorcraft Standards Staff, 
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, Rotorcraft Standards Staff.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Rotorcraft Standards Staff.

    (d) Special flight permits will not be issued.
    (e) The inspections shall be done in accordance with Eurocopter 
SA 315 Service Bulletin No. 05.34, Revision No. 1, dated September 
28, 1998. This incorporation by reference was approved by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51. Copies may be obtained from 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 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.
    (f) This amendment becomes effective on April 13, 1999.

    Note 3: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD 98-277-040(A), dated July 
15, 1998, and AD 98-277-040(A)R1, dated December 16, 1998.

    Issued in Fort Worth, Texas, on March 18, 1999.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-7384 Filed 3-26-99; 8:45 am]
BILLING CODE 4910-13-U