[Federal Register Volume 65, Number 17 (Wednesday, January 26, 2000)]
[Rules and Regulations]
[Pages 4100-4102]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-1770]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-69-AD; Amendment 39-11528; AD 2000-02-09]
RIN 2120-AA64


Airworthiness Directives; Agusta S.p.A. (Agusta) Model AB412 
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 Agusta Model AB412 helicopters with certain rescue 
hoists installed. This action requires replacing the rescue hoist hook 
assembly retention pin (retention pin) and periodically inspecting the 
rescue hoist. This amendment is prompted by an incident in which a 
rescue hoist hook assembly separated from a helicopter due to a missing 
retention pin. The actions specified in this AD are intended to prevent 
separation of the rescue hoist hook assembly from the helicopter due to 
failure of the retention pin. Loss of the rescue hoist hook assembly 
could result in loss of the person on the rescue hoist. Also, with the 
loss of the weight of the hoist cable assembly, the rescue hoist cable 
could become entangled with a main rotor or tail rotor blade, and 
result in damage or separation of a rotor blade and subsequent loss of 
control of the helicopter.

DATES:  Effective February 10, 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. 98-SW-69-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.

FOR FURTHER INFORMATION CONTACT:  Carroll Wright, Aerospace Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham 
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5120, fax (817) 
222-5961.

SUPPLEMENTARY INFORMATION:  The Registro Aeronautico Italiano (RAI), 
which is the airworthiness authority for Italy, has notified the FAA 
that an unsafe condition may exist on Agusta AB412 helicopters with 
rescue hoist, part number (P/N) BL10300-60 or P/N BL10300-59, 
installed. The RAI advises that replacement of the retention pin and 
certain inspections must be accomplished in accordance with Agusta 
Service Bulletin 412-59, Revision A, dated May 18, 1998, to prevent 
loss of a rescue hoist hook assembly. Loss of the rescue hoist hook 
assembly could result in loss of the person on the rescue hoist. Also, 
with the loss of the weight of the hoist cable assembly, the rescue 
hoist cable could become entangled with a main rotor or tail rotor 
blade, and result in damage or separation of a rotor blade and 
subsequent loss of control of the helicopter.
    The FAA has reviewed Agusta Service Bulletin 412-59, Revision A, 
dated May 18, 1998, which describes procedures for inspecting the 
rescue hoist and replacing the retention pin.
    This helicopter model is manufactured in Italy and is 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 RAI has kept the FAA informed of 
the situation described above. The FAA has examined the findings of the 
RAI, 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 Agusta Model AB412 helicopters of the same 
type design registered in the United States, this AD is being issued to 
prevent separation of the rescue hoist hook assembly from the 
helicopter due to failure of the retention pin. This AD requires, 
before further flight, replacing the retention pin, P/N BL2395, of the 
hook assembly, P/N S6150-61090-1, unless already accomplished. 
Thereafter, prior to each flight during which the rescue hoist will be 
operated, this AD requires:
     Inspecting the rescue hoist for oil leakage and proper 
electrical and mechanical connections.
     Inspecting the retention pin ring assembly for safety wire 
integrity;
     Inspecting the pin that is installed on the housing for 
absence of rotation between the housing and adapter; and
     Inspecting the rescue hoist hook to ensure it rotates 
freely relative to the housing (number 3 on Figure 1).
    This AD also requires, at intervals not to exceed 25 hours time-in-
service (TIS):
     Inspecting the rescue hoist attachment and support for 
cracks, wear, corrosion, damage, and security;
    Inspecting the rescue hoist cable for fraying, wear, and 
corrosion; and
     Inspecting the rescue hoist cable for proper routing 
through the guide rollers, pulley, and drum.
     Finally, this AD requires, at intervals not to exceed 12 
calendar months:
     Inspecting the retention pin for scratches or 
deformations, and replacing the retention pin if scratches or 
deformations are found.
    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
safe operation of the rescue hoist. Therefore, the inspections are 
required prior to further flight, and this AD must be issued 
immediately.
    None of the Agusta Model AB412 helicopters affected by this action 
are on the U.S. Register. All helicopters included in the applicability 
of this rule are operated by non-U.S. operators under foreign registry; 
therefore, they are not directly affected by this AD action. However, 
the FAA considers that this rule is necessary to ensure that the unsafe 
condition is addressed in the event that any of these subject 
helicopters are imported and placed on the U.S. Register in the future.
    Should an affected helicopter be imported and placed on the U.S. 
Register in the future, it would require approximately 2.5 work hours 
to accomplish all of the corrective actions (replacing the retention 
pin and inspecting) initially, at an average labor rate of $60 per work 
hour. Required parts would cost $85. Based on these figures, the cost 
impact of this AD would be $235 per helicopter.
    Since this AD action does not affect any helicopter that is 
currently on the U.S. Register, it has no adverse economic impact and 
imposes no additional burden on any person. Therefore, notice and 
public procedures hereon are unnecessary and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register.

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

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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-69-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 final rule does not have federalism 
implications under Executive Order 13132.
    The FAA has determined that notice and public comment are 
unnecessary in promulgating this regulation; therefore, it can be 
issued immediately to correct an unsafe condition in aircraft since 
none of these model helicopters are registered in the United States. 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, 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 2000-02-09  Agusta: Amendment 39-11528. Docket No. 98-SW-69-AD.
    Applicability: Model AB412 helicopters with rescue hoist, part 
number BL10300-60 or BL10300-59, 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 separation of the rescue hoist hook assembly from the 
helicopter due failure of the rescue hoist hook assembly retention 
pin (retention pin), accomplish the following:
    (a) Before further flight, replace the retention pin, part 
number (P/N) BL2395, of the rescue hoist hook assembly, P/N S6150-
61090-1, as follows:
    (1) Disconnect the helicopter battery and ensure the external 
electrical power is not connected.
    (2) Remove the safety wire and remove and discard the retention 
pin. Retain the two washers, P/N AN960C816L, for reuse (Figure 1).
    (3) Install a zero-hours time-in-service (TIS) retention pin, P/
N BL2395, and the two washers, P/N AN960C816L, (Figure 1). Safety 
wire the retention pin to the hook assembly using safety wire, P/N 
MS 20995C32.
    (b) Before further flight, and thereafter prior to each flight 
in which the rescue hoist will be operated:
    (1) Inspect the rescue hoist for oil leakages and proper 
electrical and mechanical connections.
    (2) Inspect the retention pin, P/N BL2395, of the ring assembly, 
P/N BL2441, for safety wire integrity.
    (3) Inspect the pin, P/N NAS516C4-6 or P/N MS171524, installed 
on the housing, P/N BL1357-1, and verify the absence of any rotation 
between the housing and the adapter, P/N BL1355, (Figure 1).
    (4) Inspect the rescue hoist hook to ensure it rotates freely 
relative to the housing (number 3 on Figure 1).
    (5) Correct any discrepancies found in step (1), (2), (3), or 
(4).
    (c) At intervals not to exceed 25 hours time-in-service (TIS), 
inspect the rescue hoist as follows:
    (1) Inspect the attachment and support for cracks, wear, 
corrosion, damage, and security. Replace any parts that have cracks, 
wear, corrosion, or damage with an airworthy part.
    (2) Inspect the cable for fraying, wear, and corrosion. If 
fraying, wear, or corrosion is found, replace the cable with an 
airworthy cable.
    (3) Inspect the cable for proper routing through the guide 
rollers, pulley, and drum. Correct cable routing if necessary.
    (d) At intervals not to exceed 12 calendar months, inspect the 
retention pin as follows:
    (1) Referring to Figure 1, remove the safety wire and the 
retention pin. Retain the two washers, P/N AN960C816L, for re-use. 
Inspect the retention pin for scratches or deformations. If a 
scratch or deformation is found, replace the retention pin with an 
airworthy retention pin.
    (2) Install the retention pin and the two washers, P/N 
AN960C816L, (Figure 1). Safety wire the retention pin to the hook 
assembly using safety wire, P/N MS20995C32.
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[GRAPHIC] [TIFF OMITTED] TR26JA00.002

    (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, FAA, Regulations Group, 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, 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.

    (f) This amendment becomes effective on February 10, 2000.

    Note 3:
     The subject of this AD is addressed in Registro Aeronautico 
Italiano (Italy) AD 98-186, dated May 26, 1998.


    Issued in Fort Worth, Texas, on January 19, 2000.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-1770 Filed 1-25-00; 8:45 am]
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