[Federal Register Volume 63, Number 74 (Friday, April 17, 1998)]
[Rules and Regulations]
[Pages 19183-19184]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-10175]



[[Page 19183]]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-09-AD; Amendment 39-10479; AD 98-04-40]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA.315B, 
SA.316B, SA.316C, SA.319B, and SE.3160 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This document publishes in the Federal Register an amendment 
adopting Airworthiness Directive (AD) 98-04-40 which was sent 
previously to all known U.S. owners and operators of Eurocopter France 
Model SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 helicopters by 
individual letters. This AD requires, for certain blades, inspecting 
each blade spar for cracks using a dye-penetrant inspection, and 
visually inspecting each blade cuff for cracks. If a crack is 
discovered in either a blade spar or cuff, removal and replacement of 
the blade with an airworthy blade is required prior to further flight. 
This amendment is prompted by an accident in which a Model SA.315B 
helicopter lost a main rotor blade (blade) just prior to take-off. The 
cause of the blade failure was determined to be fatigue cracks that 
originated from the outboard blade-to-cuff attachment bolt hole and 
progressed through the blade spar and cuff. This condition, if not 
corrected, could result in separation of a blade and subsequent loss of 
control of the helicopter.

DATES: Effective May 4, 1998, to all persons except those persons to 
whom it was made immediately effective by priority letter AD 98-04-40, 
issued on February 12, 1998, which contained the requirements of this 
amendment.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 4, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before June 16, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 98-SW-09-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.
    The applicable service information 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: Mr. Shep Blackman, Aerospace Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham 
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5296, fax (817) 
222-5961.

SUPPLEMENTARY INFORMATION: On February 12, 1998, the FAA issued 
priority letter AD 98-04-40, applicable to Eurocopter France Model 
SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 helicopters, which 
requires, for blades with 400 or more hours time-in-service (TIS), 
within 25 hours TIS, inspecting each blade spar for cracks using a dye-
penetrant method, and visually inspecting each blade cuff for cracks 
using a 10-power or higher magnifying glass. If a crack is discovered 
in either a blade spar or cuff, removal and replacement of the blade 
with an airworthy blade is required prior to further flight. That 
action was prompted by an accident in which a Model SA.315B helicopter 
lost a main rotor blade (blade) just prior to take-off. Although the 
main gearbox and the remainder of the main rotor assembly separated 
from the helicopter and passed through the cockpit, there were no 
fatalities. The cause of the blade failure was determined to be fatigue 
cracks that originated from the outboard blade-to-cuff attachment bolt 
hole and progressed through the blade spar and cuff. This condition, if 
not corrected, could result in separation of a blade and subsequent 
loss of control of the helicopter.
    The FAA has reviewed Eurocopter France Service Telex No. 00055/
0034/98, dated February 3, 1998 (Eurocopter Service Telex: 316/319 No. 
01-64 and 315 No. 01-29), which describes procedures for inspecting 
each blade spar for cracks using a dye-penetrant method, and visually 
inspecting each blade cuff for cracks using a 10-power or higher 
magnifying glass. Additionally, the Direction Generale De L'Aviation 
Civile, which is the airworthiness authority for France, has issued AD 
98-088-055(A) and 98-089-038(A), both dated February 25, 1998, to 
mandate these actions.
    Since the unsafe condition described is likely to exist or develop 
on other Eurocopter France Model SA.315B, SA.316B, SA.316C, SA.319B, 
and SE.3160 helicopters of the same type design, the FAA issued 
priority letter AD 98-04-40 to prevent separation of a blade and 
subsequent loss of control of the helicopter. The AD requires, for 
blades with 400 or more hours time-in-service (TIS), within 25 hours 
TIS, inspecting each blade spar for cracks using a dye-penetrant 
method, and visually inspecting each blade cuff for cracks using a 10-
power or higher magnifying glass. If a crack is discovered in either a 
blade spar or cuff, removal and replacement of the blade with an 
airworthy blade is required prior to further flight. The actions are 
required to be accomplished in accordance with the service telex 
described previously.
    Since it was found that immediate corrective action was required, 
notice 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 February 12, 1998 to all known U.S. owners and operators of 
Eurocopter France Model SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 
helicopters. These conditions still exist, and the AD is hereby 
published in the Federal Register as an amendment to section 39.13 of 
the Federal Aviation Regulations (14 CFR 39.13) to make it effective to 
all persons.
    The FAA estimates that 106 helicopters of U.S. Registry will be 
affected by this AD, that it will take approximately 4 work hours per 
helicopter to inspect each helicopter and 4 work hours to replace a 
main rotor blade, and that the average labor rate is $60 per work hour. 
Required parts will cost approximately $49,700 per helicopter. Based on 
these figures, the total cost impact of this AD on U.S. operators is 
estimated to be $5,319,080, assuming one blade replacement 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

[[Page 19184]]

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-09-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 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:

98-04-40  Eurocopter France: Amendment 39-10479. Docket No. 98-SW-
09-AD.

    Applicability: Model SA.315B, SA.316B, SA.316C, SA.319B, and 
SE.3160 helicopters, with main rotor blades, part numbers 3160S11-
10000 all dash numbers, 3160S11-30000 all dash numbers, 3160S11-
35000 all dash numbers, 3160S11-40000 all dash numbers, 3160S11-
45000 all dash numbers, 3160S11-50000 all dash numbers, 3160S11-
55000 all dash 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 
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 use the authority 
provided in paragraph (d) to request approval from the FAA. This 
approval may address either no action, if the current configuration 
eliminates the unsafe condition, or different actions necessary to 
address the unsafe condition described in this AD. Such a request 
should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any helicopter from the applicability of this AD.
    Compliance: Required as indicated, unless accomplished 
previously, for helicopters with main rotor blades (blades) having 
400 or more hours time-in-service (TIS).
    To prevent separation of a blade and subsequent loss of control 
of the helicopter, accomplish the following:
    (a) Within 25 hours TIS, inspect each blade spar for cracks 
using a dye-penetrant method in accordance with paragraphs CC.1 
through CC.4 of the Operational Procedures in Eurocopter France 
Service Telex No. 00055/0034/98, dated February 3, 1998 (Eurocopter 
Service Telex: 316/319 No. 01-64 and 315 No. 01-29).
    (b) Within 25 hours TIS, visually inspect the upper and lower 
surfaces of each blade cuff for cracks, especially around the 
attachment pins, using a 10-power or higher magnifying glass.
    (c) If a crack is found in a blade spar or cuff, remove the 
blade and replace it with an airworthy blade prior to further 
flight.
    (d) 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.

    (e) Special flight permits will not be issued.
    (f) The inspection shall be done in accordance with paragraphs 
CC.1 through CC.4 of the Operational Procedures in Eurocopter France 
Service Telex No. 00055/0034/98, dated February 3, 1998 (Eurocopter 
Service Telex: 316/319 No. 01-64 and 315 No. 01-29). 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.
    (g) This amendment becomes effective on May 4, 1998, to all 
persons except those persons to whom it was made immediately 
effective by Priority Letter AD 98-04-40, issued February 12, 1998, 
which contained the requirements of this amendment.

    Note 3: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD 98-088-055(A) and 98-089-
038(A), dated February 25, 1998.

    Issued in Fort Worth, Texas, on April 3, 1998.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-10175 Filed 4-16-98; 8:45 am]
BILLING CODE 4910-13-U