AD 2000-05-17

[Federal Register Volume 65, Number 51 (Wednesday, March 15, 2000)]
[Rules and Regulations]
[Pages 13875-13877]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-6034]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-85-AD; Amendment 39-11627; AD 2000-05-17]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model EC 120B 
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 France Model EC 120B helicopters, that 
currently requires, at specified time intervals, inspecting the engine 
coupling tube for cracks and replacing any cracked engine coupling tube 
with an airworthy engine coupling tube. This amendment requires, at 
specified time intervals, visually inspecting and dye-penetrant 
inspecting the coupling tube for any crack and replacing any cracked 
coupling tube with a reinforced, airworthy coupling tube. Replacing all 
coupling tubes and certain engine support fitting components is 
required on or before March 31, 2000. This amendment is prompted by the 
discovery of cracks in several coupling tubes. The actions specified by 
this AD are intended to prevent coupling failure, loss of engine drive, 
and a subsequent forced landing.

DATES: Effective March 27, 2000. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of March 27, 2000.
    Comments for inclusion in the Rules Docket must be received on or 
before May 15, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 99-SW-85-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: Shep Blackman, Aerospace Engineer, 
Regulations Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., 
Fort Worth, Texas 76137, telephone (817) 222-5296, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: On September 2, 1999, the FAA issued 
Emergency Priority Letter AD 99-19-23 and on September 22, 1999, issued 
the final rule; request for comments for AD 99-19-23, Amendment 39-
11343 (64 FR 53623, October 4, 1999), to require within 10 hours time-
in-service (TIS), and thereafter, at intervals not to exceed 10 hours 
TIS, inspecting a specified engine coupling tube for cracks and 
replacing any cracked engine coupling tube with an airworthy engine 
coupling tube. That action was prompted by the discovery, during 
routine maintenance inspections, of three cracked engine coupling tubes 
caused by structural resonance. That condition, if not corrected, could 
result in coupling failure, loss of engine drive, and a subsequent 
forced landing.
    Since the issuance of that AD, the manufacturer has issued 
Eurocopter Service Bulletin No. 05-001, dated September 23, 1999, which 
introduces a new alternative check procedure. The Direction Generale de 
L'Aviation Civile (DGAC), which is the airworthiness authority for 
France, classified this service bulletin as mandatory and issued AD 
1999-349-002(A) R2, dated November 3, 1999, to ensure the continued 
airworthiness of these helicopters in France. The manufacturer has also 
issued Eurocopter Service Bulletin No. 63-001, dated November 10, 1999, 
which recommends installing a reinforced coupling tube and 
disassembling the engine mount fitting assembly. The manufacturer then 
issued Eurocopter Service Bulletin No. 01-002, dated December 23, 1999, 
which declares that coupling tubes, P/N C631A1002101, and certain 
engine support fitting components are unfit for flight after March 31, 
2000. The DGAC classified this service bulletin as mandatory and issued 
AD 2000-058-

[[Page 13876]]

003(A), dated February 9, 2000, to ensure the continued airworthiness 
of these helicopters in France.
    This helicopter model is manufactured in France and is type 
certificated for operation in the United States under the provision 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 this type design that are 
certificated for operations in the United States.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other Eurocopter France Model EC 120B helicopters 
of the same type design, this AD supersedes AD 99-19-23 to require 
periodic visual and dye-penetrant inspections on each coupling tube, 
replacement of any cracked coupling tube, and replacement of the 
coupling tube and certain engine mount fitting components on or before 
March 31, 2000. The actions must be accomplished in accordance with the 
service bulletins described previously. 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 actions stated previously must be 
accomplished at the specified time intervals, 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 12 helicopters will be affected by this 
proposed AD, that it will take approximately 1 work hour to visually 
inspect each coupling tube and 6.5 work hours to dye-penetrant inspect 
each coupling tube. Replacing each coupling tube and installing the 
engine mount fitting components will take approximately 12 work hours 
per helicopter. The average labor rate is $60. The manufacturer states 
that they will provide the components necessary for replacing the 
coupling tubes free of charge. Based on these figures and the 
manufacturer's representation that it will provide the repair parts 
free of charge, the total cost impact of the AD on U.S. operators is 
estimated to be $19,400, assuming 2 visual inspections, 2 dye-penetrant 
inspections, 1 coupling tube replacement, and 1 installation of the 
engine support fitting components on each 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. 99-SW-85-09AD.'' The postcard will be date stamped and 
returned to the commenter.
    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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 removing Amendment 39-11343 (64 FR 
53623, October 4, 1999), and by adding a new airworthiness directive 
(AD), Amendment 39-11627, to read as follows:

AD 2000-05-17  Eurocopter France: Amendment 39-11627. Docket No. 99-
SW-85-AD. Supersedes AD 99-19-23, Amendment 39-11343, Docket No. 99-
SW-53-AD.

    Applicability: Model EC 120B helicopters with engine coupling 
tube (coupling tube), part number (P/N) C631A1002101, 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 prevent coupling failure, loss of engine drive, and a 
subsequent forced landing, accomplish the following:

[[Page 13877]]

    (a) Within 10 hours time-in-service (TIS), and thereafter at 
intervals not to exceed 10 hours TIS except when required to perform 
the inspection required by paragraph (b) of this AD while each 
coupling tube, P/N C631A1002101, is installed, inspect for any crack 
in accordance with the Accomplishment Instructions, paragraph 
2.B.1., of Eurocopter Service Bulletin No. 05-001, dated September 
23, 1999 (SB 05-001).
    (b) Within 10 hours TIS, and thereafter at intervals not to 
exceed 30 hours TIS, after each coupling tube, P/N C631A1002101, has 
been removed, inspect for any crack in accordance with paragraph 
2.B.2. of SB 05-001.

    Note 2: Operators are not required to inform the manufacturer 
when a crack is found.

    (c) When a crack is found as a result of the inspections 
conducted in accordance with either paragraph (a) or (b) of this AD, 
or by March 31, 2000, whichever occurs first, replace the coupling 
tube with a reinforced, airworthy coupling tube, P/N C631A1101101, 
and replace the engine mount fittings in accordance with Eurocopter 
Service Bulletin No. SB 63-001, dated November 10, 1999, using new, 
airworthy, engine mount fitting components to replace the following:
    <bullet> Teflon spacer, P/N C714A1010208;
    <bullet> Black-colored spring washers, 10.2 x 28 Type-C;
    <bullet> Blue-colored hinge yoke, P/N C714A1010212; and
    <bullet> Special washer, P/N C714A1010213.

    Note 3: Eurocopter Service Bulletin No. 01-002 pertains to 
unairworthiness of the four engine mount fitting components listed 
in paragraph (c) of this AD.

    (d) Installing the reinforced, airworthy coupling tubes, P/N 
C631A1101101, and replacing the engine mount fitting components 
using new, airworthy, engine mount fitting components, as specified 
in paragraph (c) of this AD, constitutes terminating action for the 
requirements of this AD.
    (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, Regulations Group, 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, Regulations Group.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (f) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the helicopter to a location where the 
requirements of this AD can be accomplished.
    (g) The inspections and modifications shall be done in 
accordance with the Accomplishment Instructions, paragraph 2.B.1., 
of Eurocopter Service Bulletin No. 05-001, dated September 23, 1999; 
Eurocopter Service Bulletin No. 63-001, dated November 10, 1999; and 
Eurocopter Service Bulletin No. 01-002, dated December 23, 1999. 
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.
    (h) This amendment becomes effective on March 27, 2000.

    Note 5: The subject of this AD is addressed in Direction 
Generale de L'Aviation Civile (France) AD 1999-349-002(A) R2, dated 
November 3, 1999 and AD 2000-058-003(A), dated February 9, 2000.


    Issued in Fort Worth, Texas, on March 6, 2000.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-6034 Filed 3-14-00; 8:45 am]
BILLING CODE 4910-13-U