[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]
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