[Federal Register Volume 65, Number 16 (Tuesday, January 25, 2000)]
[Rules and Regulations]
[Pages 3796-3798]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-1369]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-74-AD; Amendment 39-11517; AD 2000-01-19]
RIN 2120-AA64


Airworthiness Directives; Eurocopter Deutschland GMBH Model EC 
135 P1 and EC 135 T1 Helicopters

AGENCY:  Federal Aviation Administration, DOT.

ACTION:  Final rule; request for comments.

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

SUMMARY:  This amendment adopts a new airworthiness directive (AD) 
applicable to Eurocopter Deutschland GMBH (ECD) Model EC 135 P1 and EC 
135 T1 helicopters. This action requires inspecting main rotor 
expansion bolt safety wires, bolt heads, and bolt nuts; replacing any 
unairworthy expansion bolt with a hexagon bolt; and, as necessary, 
replacing any bolt nut before further flight. This AD also requires 
replacing each expansion bolt, regardless of condition, no later than 
January 31, 2000. This amendment is prompted by reports of main rotor 
blade expansion bolt nuts becoming loose. This condition, if not 
corrected, could result in severe vibration during flight and 
subsequent loss of control of the helicopter.

DATES:  Effective February 4, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 4, 2000.
    Comments for inclusion in the Rules Docket must be received on or 
before March 27, 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-74-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas.
    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, Room 663, Fort Worth, Texas.

FOR FURTHER INFORMATION CONTACT:  Richard A. Monschke, Aerospace 
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort 
Worth, Texas 76193-0110, telephone (817) 222-5116, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION:  Luftfahrt-Bundesamt (LBA), the 
airworthiness authority for the Federal Republic of Germany, notified 
the FAA that an unsafe condition may exist on Model EC 135 P1 and EC 
135 T1 helicopters. The LBA advises that severe vibrations occurred 
during a helicopter flight due to an expansion bolt nut becoming loose.
    ECD has issued Alert Service Bulletin EC135-62A-005, Revision 1, 
dated November 16, 1999 (ASB). The ASB specifies inspecting the safety 
wire, bolt head, and bolt nut for the extent of thread protrusion of 
the expansion bolt through the end of the nut; replacing the expansion 
bolt by a hexagon bolt as necessary; and replacing the nut as 
necessary. In addition, all hexagon bolts must replace all expansion 
bolts no later than January 31, 2000. The LBA classified this ASB as 
mandatory and issued AD 1999-264, dated July 2, 1999, to ensure the 
continued airworthiness of these helicopters in the Federal Republic of 
Germany.
    These helicopter models are manufactured in the Federal Republic of 
Germany 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 LBA 
has kept the FAA informed of the situation described above. The FAA has 
examined the findings of the LBA, 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 ECD Model EC 135 P1 and EC 135 T1 helicopters 
of the same type designs registered in the United States, this AD is 
being issued to prevent a main rotor blade expansion bolt from becoming 
loose, severe vibration during flight, and subsequent loss of control 
of the helicopter. This AD requires, before further flight and at 
intervals not to exceed 15 hours time-in-service (TIS), inspecting the 
main rotor blade expansion bolt safety wire, bolt head, and bolt nut 
for the extent of thread protrusion of the expansion bolt through the 
end of the nut; replacing any unairworthy expansion bolt with a hexagon 
bolt; and replacing the nut as necessary. The AD also requires 
replacing all expansion bolts, part number (P/N) L621M1010 223, with 
hexagon bolts, P/N L621M1010 222, before further flight after January 
31, 2000. The actions are required to be accomplished in accordance 
with the ASB 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, inspecting the main rotor blade expansion bolt safety wire, 
bolt head, and bolt nut; replacing any unairworthy expansion bolt with 
a hexagon bolt; and replacing the nut as necessary is required before 
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 AD, 
that it will take approximately 10 work hours to

[[Page 3797]]

accomplish inspecting and replacing the parts, and that the average 
labor rate is $60 per work hour. The ECD ASB states that the 
replacement parts kit, P/N EC 135-62A-005-2.C, will be provided on 
request to ECD at no cost. Based on these figures, the total cost 
impact of the AD on U.S. operators is estimated to be $8,400.

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-74-AD.'' 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 proposal 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 adding a new airworthiness directive 
to read as follows:

AD 2000-01-19  Eurocopter Deutschland GMBH: Amendment 39-11517. 
Docket No. 99-SW-74-AD.

    Applicability: Model EC 135 P1 and EC 135 T1 helicopters, with 
main rotor blades up to and including serial number 834, 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 (d) 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 a main rotor blade expansion bolt nut becoming loose, 
causing severe vibration during flight, and subsequent loss of 
control of the helicopter, accomplish the following:
    (a) Before further flight and thereafter at intervals not to 
exceed 15 hours time-in-service, visually inspect the main rotor 
blade expansion bolt safety wire, bolt head, and bolt nut in 
accordance with the Accomplishment Instructions, paragraph 3.A., 
steps (1), (2), (3), (4), and (6) of Eurocopter Deutschland GMBH 
(ECD) Alert Service Bulletin EC 135-62A-005, Revision 1, dated 
November 16, 1999 (ASB). If the safety wire is improperly fitted, 
the bolt head is worn, the expansion bolt thread does not protrude 
through the end of the nut, the bolt head has metallic abrasions, 
the nut is loose, or the nut has metallic abrasions, before further 
flight, replace the expansion bolt, part number (P/N) L621M1010 223, 
with a hexagon bolt, P/N L621M1010 222, and, as necessary, replace 
the nut in accordance with paragraph 3.B. of the ASB.
    (b) Replace all expansion bolts, P/N L621M1010 223, with hexagon 
bolts, P/N L621M1010 222, and, as necessary, replace the nuts before 
flight after January 31, 2000.
    (c) Replacing the expansion bolts with hexagon bolts and 
replacing the nuts, as necessary, constitutes terminating action for 
the requirements of this AD.
    (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, 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 2:  Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (e) Special flight permits will not be issued.
    (f) The inspection and replacement of the main rotor blade bolts 
shall be done in accordance with the Accomplishment Instructions, 
paragraph 3.A., Eurocopter Deutschland GMBH Alert Service Bulletin 
EC 135-62A-005, Revision 1, dated November 16, 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, 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 February 4, 2000.

    Note 3:  The subject of this AD is addressed in Luftfahrt-
Bundesamt (the Federal Republic of Germany) AD 1999-264, dated July 
2, 1999.


[[Page 3798]]



    Issued in Fort Worth, Texas, on January 11, 2000.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-1369 Filed 1-24-00; 8:45 am]
BILLING CODE 4910-13-U