[Federal Register Volume 64, Number 66 (Wednesday, April 7, 1999)]
[Rules and Regulations]
[Pages 16808-16810]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-8409]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-58-AD; Amendment 39-11112; AD 99-08-06]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA. 3160, SA. 
316B, SA. 316C, and SA. 319B 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. 3160, SA. 316B, SA. 316C, 
and SA. 319B helicopters. This action requires inspecting the spar skin 
and main rotor blade (blade) root reinforcement strip area for a 
bonding separation, corrosion, or a crack, and replacing the blade, if 
necessary. This amendment is prompted by the in-flight failure of a 
blade. The actions specified in this AD are intended 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 
subsequent loss of control of the helicopter.

DATES: Effective April 22, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 22, 1999.
    Comments for inclusion in the Rules Docket must be received on or 
before May 7, 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-58-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)

[[Page 16809]]

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:

Basis for Issuing This AD

    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 SE. 3160, SA. 316B, SA. 316C, and 
SA. 319B 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 316/319 Service Bulletin 
No. 05.92 Revision No. 1, dated September 28, 1998 (SB). That SB 
specifies an inspection for bonding separation in the area along the 
reinforcement strip using a tapping method, 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 service bulletin as 
mandatory and issued DGAC AD 98-285-057(A), dated July 15, 1998, and 
DGAC AD 98-285-057(A) R1, dated December 16, 1998, in order to assure 
the continued airworthiness of these helicopters in France. The DGAC 
AD's require the initial inspection within 25 flying hours or 6 months, 
the Eurocopter SB recommends the initial inspection within 25 hours. 
The FAA has determined that the initial inspection must be accomplished 
before further flight to ensure public safety.
    These helicopter models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 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 these type designs that are 
certificated for operation in the United States. Since an unsafe 
condition has been identified that is likely to exist or develop on 
other Eurocopter France Model SE. 3160, SA. 316B, SA. 316C, and SA. 
319B helicopters of the same type designs 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 a blade and subsequent 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 any bonding 
separation, corrosion, or a crack is found. The actions are required to 
be accomplished in accordance with the service bulletin described 
previously. The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
structural integrity of the helicopters. 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 calendar months, whichever occurs first, and this AD 
must be issued immediately.
    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 not practical, and that good cause exists 
for making this amendment effective in less than 30 days.

Cost Impact

    The FAA estimates that 24 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 $2,160 to 
conduct one inspection of the fleet, and $40,960 per helicopter to 
replace one blade (if necessary).

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-58-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.

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

[[Page 16810]]

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 99-08-06  Eurocopter France: Amendment 39-11112. Docket No. 98-
SW-58-AD.

    Applicability: Model SE. 3160, SA. 316B, SA. 316C, and SA. 319B 
helicopters, with main rotor blade, part numbers (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, and 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 (e) 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 cracks in the area 
of a main rotor blade (blade) root reinforcement strip, which could 
result in failure of the blade and subsequent loss of control of the 
helicopter, accomplish the following:
    (a) Before further flight, and afterwards at intervals not to 
exceed 100 hours time-in-service or 6 calendar months, whichever 
occurs first, inspect the spar skin and blade root reinforcement 
strip area for a bonding separation, corrosion, or a crack in 
accordance with paragraphs 2.A and 2.B of the Accomplishment 
Instructions in Eurocopter SA 316/319 Service Bulletin No. 05.92. 
Revision No. 1, dated September 28, 1998 (SB), except operators are 
not required to contact Eurocopter if an anamoly is found.
    (b) For the hatched areas (1.5 x 50mm and 10 x 100mm) on the 
upper and lower surfaces of each blade, if bonding separation is 
found, replace the blade with an airworthy blade prior to further 
flight (refer to Figure 1 of the SB).
    (c) Bonding separation in the non-hatched area (10 x 100mm) of 
the upper and lower surfaces of each blade is permissible and must 
be inspected using the tapping method at intervals not to exceed 25 
hours time-in-service to monitor possible propagation. When the 
bonding separation reaches the hatched area, the blade must be 
replaced with an airworthy blade (refer to Figure 1 of the SB).
    (d) 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).
    (e) 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, 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, Standards Staff.

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

    (f) Special flight permits will not be issued.
    (g) Accomplish the inspections in accordance with Eurocopter SA 
316/319 Service Bulletin No. 05.92 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.
    (h) This amendment becomes effective on April 22, 1999.

    Note 3: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD 98-285-057(A), dated July 
15, 1998, and AD 98-285-057(A)R1, dated December 16, 1998.

    Issued in Fort Worth, Texas, on March 30, 1999.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-8409 Filed 4-6-99; 8:45 am]
BILLING CODE 4910-13-U