[Federal Register Volume 64, Number 81 (Wednesday, April 28, 1999)]
[Rules and Regulations]
[Pages 22782-22784]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-10349]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-54-AD; Amendment 39-11150; AD 99-09-16]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France (Eurocopter) Model SE 
3130, SE 313B, SA 3180, SA 318B, and SA 318C Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to Eurocopter Model SE 3130, SE 313B, SA 3180, SA 
318B, and SA 318C helicopters, that currently requires a visual 
inspection of the main rotor blade reinforcement strips for debonding 
between the reinforcement strips of the blade; and a visual inspection 
of the main rotor blade (blade) skin for cracks or corrosion, and 
replacement of the blade with an airworthy blade if certain debonding 
or a crack or corrosion is found. This amendment requires additional 
inspections using a tapping method, redefines the area to be inspected, 
and increases the repetitive inspection interval. This amendment is 
prompted by an in-flight failure of a main rotor blade on a Eurocopter 
SE 3130 helicopter. The actions specified by this AD are intended to 
detect bonding separation, cracks, or corrosion in the area of the 
blade root reinforcement

[[Page 22783]]

strip, and to prevent failure of a blade and subsequent loss of control 
of the helicopter.

DATES: Effective May 13, 1999. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of May 13, 1999.
    Comments for inclusion in the Rules Docket must be received on or 
before June 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-54-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 
76137; 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, 
Rotorcraft Standards Staff, 2601 Meacham Blvd., Fort Worth, Texas 
76137, telephone (817) 222-5116, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: On November 14, 1997 the FAA issued AD 97-
24-04, Amendment 39-10211 (62 FR 62239, November 21, 1997), to require 
a visual inspection of each main rotor blade reinforcement strip for 
debonding between the reinforcement strips of a blade; and a visual 
inspection of the blade skin for cracks or corrosion, and replacement 
of the blade with an airworthy blade if certain debonding or a crack or 
corrosion is found. That action was prompted by an accident in which a 
blade separated in flight due to fatigue cracks in the blade that 
initiated from skin debonding or corrosion. That condition, if not 
corrected, could result in failure of a blade in flight and subsequent 
loss of control of the helicopter.
    Since the issuance of that AD, Eurocopter has issued Eurocopter 
Service Bulletin No. 05.91, Revision No. 1, dated September 28, 1998, 
which provides more detailed procedures for performing the inspections 
required in the AD by requiring a tapping test and increases the 
repetitive inspection intervals from 25 hours time-in-service (TIS) to 
100 hours TIS or 6 calendar months, whichever occurs first.
    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 Direction Generale De L'Aviation 
Civile, (DGAC) which is the airworthiness authority for France, 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.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other Eurocopter Model SE 3130, SE 313B, SA 3180, 
SA 318B, and SA 318C helicopters of the same type design, this AD 
supersedes AD 97-24-04 to require, before further flight, and 
thereafter, at intervals not to exceed 100 hours time-in-service or 6 
calendar months, whichever occurs first, an inspection of each blade 
spar skin and blade root reinforcement area for bonding separations, 
cracks, or corrosion, and replacement with an airworthy blade if any 
bonding separation, crack, or corrosion 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 controllability and structural integrity of the 
helicopter. Therefore the inspection and replacement, if necessary, is 
required prior to further flight 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 hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.
    The FAA estimates that 14 helicopters will be affected by this 
proposed AD, that it will take approximately 1.5 work hours to 
accomplish the inspections and 16 work 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 replacement blade. 
Based on these figures, the total cost impact of the AD on U.S. 
operators is estimated to be $88,220, assuming 5 inspections per 
helicopter, per year, and 2 main rotor blade replacements for the 
entire fleet.

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-54-AD.'' The postcard will be date stamped and 
returned to the commenter.
    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 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

[[Page 22784]]

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 removing Amendment 39-10211 (62 FR 
62239, November 21, 1997), and by adding a new airworthiness directive 
(AD), Amendment 39-11150, to read as follows:

AD 99-09-16  Eurocopter France: Amendment 39-11150. Docket No. 98-
SW-54-AD. Supersedes AD 97-24-04, Amendment 39-10211, Docket No. 97-
SW-22-AD.

    Applicability: Model SE 3130, SE 313B, SA 3180, SA 318B, and SA 
318C helicopters with main rotor blades, part number (P/N) 3130S11-
10000-all part numbers, 3130S11-20000-all part numbers, or 3130S11-
30000-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 prevent failure of a main rotor blade (blade) in flight and 
subsequent 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 calendar months, 
whichever occurs first, inspect each blade spar skin and blade root 
reinforcement strip area for bonding separations, cracks, or 
corrosion in accordance with paragraphs 2.A. and 2.B. of the 
Accomplishment Instructions of Eurocopter Service Bulletin No. 05.91 
Revision No. 1, dated September 28, 1998 (SB). Notification to 
Eurocopter La Courneuve, Department E/SRPT is not required.
    (1) For the hatched areas (15 x 95mm and 8 x 95mm) 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 
(see Figure 1 of the SB).
    (2) Bonding separation in the non-hatched area (8 x 95mm) of the 
upper and lower surfaces of each blade is permissible but must be 
inspected using the tapping method at intervals not to exceed 25 
hours TIS in order to monitor possible propagation. If the bonding 
separation reaches the hatched area, the blade must be replaced with 
an airworthy blade before further flight (see Figure 1 of the SB).
    (b) Before further flight, and thereafter at intervals not to 
exceed 100 hours TIS or 6 calendar months, whichever occurs first, 
visually inspect for bonding separation, a crack, or corrosion on 
the upper and lower skin in the 100 x 95mm blade root area (see 
Figure 1 of the SB). If a bonding separation in the hatched area, a 
crack, or corrosion is detected, replace the blade with an airworthy 
blade prior to further flight.
    (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, FAA, 
Rotorcraft Directorate. 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 inspection and replacement, if necessary, shall be done 
in accordance with the Accomplishment Instructions of Eurocopter 
Service Bulletin No. 05.91 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 American 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 May 13, 1999.

    Note 3: The subject of this AD is addressed in Direction 
Generale de L'Aviation Civile (France) AD 97-135-055(A) R1, dated 
July 15, 1998 and AD 97-135-055(A)R2, dated December 16, 1998.

    Issued in Fort Worth, Texas, on April 16, 1999.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-10349 Filed 4-27-99; 8:45 am]
BILLING CODE 4910-13-P