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[Federal Register Volume 65, Number 96 (Wednesday, May 17, 2000)]
[Proposed Rules]
[Pages 31291-31293]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-12357]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-SW-10-AD]

Airworthiness Directives; Bell Helicopter Textron Canada Model 
407 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to Bell Helicopter Textron 
Canada (BHTC) Model 407 helicopters, that currently requires installing 
a tail rotor pitch-limiting left-pedal stop (pedal stop), installing an 
airspeed limitation placard, marking a never-exceed velocity (Vne) 
placard on all airspeed indicators, and revising the Limitations 
section of the Rotorcraft Flight Manual (RFM). This action would 
require installing a redesigned tail rotor system and modifying the 
vertical fin and horizontal stabilizer to allow restoring the Vne to 
140 knots indicated airspeed (IAS). This proposal is prompted by design 
changes to the tail rotor system and modification of the pedal stop for 
airspeed actuation to eliminate a tail rotor strike to the tailboom. 
The actions specified by the proposed AD are intended to prevent the 
tail rotor blades from striking the tailboom, separation of the aft 
section of the tailboom with the tail rotor gearbox and vertical fin, 
and subsequent loss of control of the helicopter.

DATES: Comments must be received on or before June 16, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2000-SW-10-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: [email protected]. 
Comments may be inspected at the Office of the Regional Counsel between 
9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal 
holidays.
    The service information referenced in the proposed rule may be 
obtained from BHTC, 12,800 Rue de l'Avenir, Mirabel, Quebec JON1LO, 
telephone (800) 463-3036, fax (514) 433-0272. This information may be 
examined at the FAA, Office of the Regional Counsel, Southwest Region, 
2601 Meacham Blvd., Room 663, Fort Worth, Texas.

FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Regulations Group, Fort Worth, 
Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed 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 above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their mailed 
comments submitted in response to this notice must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2000-SW-10-AD.'' The postcard will be date 
stamped and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2000-SW-10-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137.

Discussion

    On March 30, 1999, the FAA issued AD 99-06-15, Amendment 39-11111 
(64 FR 16801, April 7, 1999), to require installing a pedal stop and 
adjusting the rigging of the directional controls, installing an 
airspeed limitation placard, marking a new never-exceed velocity (Vne) 
limit on all airspeed indicators, and revising the Limitations section 
of the RFM. That action was

[[Page 31292]]

prompted by three accidents involving in-flight tail rotor blade 
strikes against the tailboom. The requirements of that AD are intended 
to prevent the tail rotor blades from striking the tailboom, separation 
of the aft section of the tailboom with the tail rotor gearbox and 
vertical fin, and subsequent loss of control of the helicopter.
    Since the issuance of that AD, the manufacturer has made a design 
change to the tail rotor system to eliminate tail rotor strikes to the 
tailboom, and also made design changes to the pedal stop.
    BHTC has issued Bell Helicopter Textron Alert Service Bulletin 
(ASB) No. 407-99-27, Rev. A, dated June 9, 1999, and Bell Helicopter 
Textron Technical Bulletin No. 407-99-17, dated April 15, 1999, both of 
which concern replacing the tail rotor; ASB 407-99-33, Revision A, 
dated March 10, 2000, which concerns installing a pedal stop and 
restoring the Vne to 140 knots IAS; and Bell Helicopter Textron 
Technical Bulletin No. 407-96-2, Revision A, dated March 11, 1997, 
which concerns modifying the vertical fin and horizontal stabilizer. 
Transport Canada classified these service bulletins as mandatory and 
issued AD No. CF-1998-36R7, dated February 1, 2000, in order to assure 
the continued airworthiness of these helicopters in Canada.
    This helicopter model is manufactured in Canada and is type 
certificated for operation in the United States under the provisions of 
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the 
applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, Transport Canada, which is the 
airworthiness authority for Canada, has kept the FAA informed of the 
situation described above. The FAA has examined the findings of the 
Transport Canada, 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 BHTC Model 407 helicopters of the same type 
design, the proposed AD would supersede AD 99-06-15 to require 
installing a redesigned tail rotor system, modifying the vertical fin 
and horizontal stabilizer, and restoring the Vne to 140 knots IAS.
    The FAA estimates that 200 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 80 work 
hours per helicopter to perform the modifications and installations, 
and that the average labor rate is $60 per work hour. Required parts 
would cost approximately $24,161 per helicopter; however, the 
manufacturer has stated they will provide these parts at no cost. 
Additionally, the manufacturer has stated they will reimburse the cost 
of labor up to $4,400. Based on these figures, the total cost impact of 
the proposed AD on U.S. operators is estimated to be $5,792,200 or 
$28,961 per helicopter, assuming no costs are reimbursed.
    The regulations proposed herein would 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 would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, will not have a significant economic impact, 
positive or negative, on a substantial number of small entities under 
the criteria of the Regulatory Flexibility Act. A copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting 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.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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 39-11111 (64 FR 
16801, April 7, 1999), and by adding a new airworthiness directive 
(AD), to read as follows:

Bell Helicopter Textron Canada: Docket No. 2000-SW-10-AD. Supersedes 
AD 99-06-15, Amendment 39-11111, Docket No. 99-SW-16-AD.

    Applicability: Model 407 helicopters, 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 the tail rotor blades from striking the tailboom, 
which could result in separation of the aft section of the tailboom 
with the tail rotor gearbox and vertical fin, and subsequent loss of 
control of the helicopter, accomplish the following:
    (a) Before further flight:
    (1) Install a stop that limits the maximum distance that the 
left pedal can travel in accordance with Part I of the 
Accomplishment Instructions in Bell Helicopter Textron Canada 
Technical Bulletin 407-98-13, dated December 12, 1998 (TB).
    (2) Adjust the rigging of the directional controls in accordance 
with Part II of the Accomplishment Instructions in the TB.
    (3) Install the airspeed limitation placard shown in Figure 1 of 
this AD so that it completely covers and obscures the airspeed 
limitation placard, P/N 407-070-201-103. Ensure that the replacement 
placard is at least 2\1/16\-inches tall and 3 \9/16\-inches long.

[[Page 31293]]

                                                     Figure 1.--407 Airspeed Limitations--Knots--IAS
                                                                      [AD 99-06-15]
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                               OAT                                                             Pressure altitude FX  x  1000
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                             C deg.                                  0       2       4       6       8      10      12      16      16      18      20
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52..............................................................      98      93      88
40..............................................................     100      95      91      86      81      76
20..............................................................     100     100      95      90      85      80      76      71      66      61
0...............................................................     100     100     100      95      90      85      80      75      70      65      60
-20.............................................................     100     100     100     100      95      90      85      80      75      70      65
-40.............................................................      97      93      88      83      79      74      70      65      61
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                            Maximum Autorotation VNE 100 KIAS
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    (4) Install a redline at a Vne of 100 KIAS on all airspeed 
indicators. Remove or obscure any previously installed lines or arcs 
above 100 KIAS. If the redline is installed on the instrument glass, 
also install a slippage mark on the glass and on the instrument 
case.
    (5) Add the following statement to the Limitations section of 
the Rotorcraft Flight Manual (RFM):
    When operating at an airspeed of 60 to 100 KIAS, maintain yaw 
trim within one ball diameter of the centered position of the turn 
and bank (slip) indicator, and avoid sudden or large directional 
control inputs in flight.
    (6) Mark the airspeed limitations placard in Figure 1-3 in the 
RFM to indicate that it has been superseded by this AD, and insert a 
copy of this AD into the RFM. Also, mark the airspeed indicator in 
Figure 1-5 of the RFM to indicate a Vne of 100 KIAS.
    (7) This AD revises the limitations section of BHTC Model 407 
RFM by replacing sheet 1 of Figure 1-3 in the RFM with Figure 1 of 
this AD, revising sheet 3 of Figure 1-5 of the RFM, and adding an 
operational limitation for allowable yaw trim and directional 
control input.
    (8) Report any uncommanded right yaw, uncommanded movement of 
the pedals during flight, or tail rotor blade contact with the 
tailboom within 24 hours of the occurrence to the Manager, 
Regulations Group, telephone (817) 222-5111. Reporting requirements 
have been approved by the Office of Management and Budget and 
assigned OMB control number 2120-0056.
    (b) Before further flight after January 31, 2001:
    (1) Remove and replace the existing tail rotor with tail rotor 
installation, P/N 407-012-100-109, in accordance with Part II of 
Bell Helicopter Textron Technical Bulletin 407-99-17, dated April 
15, 1999.
    (2) Modify the vertical fin and horizontal stabilizer in 
accordance with Bell Helicopter Textron Technical Bulletin No. 407-
96-2, Revision A, dated March 11, 1997.
    (3) Install the tail rotor airspeed-actuated pedal stop kit, 
install the new airspeed limitation decals, and remove the temporary 
instrument markings and RFM changes in accordance with the 
Accomplishment Instructions in Parts I, II, and III of Bell 
Helicopter Textron Alert Service Bulletin 407-99-33, Revision A, 
dated March 10, 2000.
    (c) Accomplishing the requirements of paragraph (b) of this AD 
is 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 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.

    Note 3: The subject of this AD is addressed in Transport Canada 
(Canada) AD CF-98-36R7, dated February 1, 2000.

    Issued in Fort Worth, Texas, on May 5, 2000.
Eric Bries,
Acting Manager, Rotorcraft Directorate,, Aircraft Certification 
Service.
[FR Doc. 00-12357 Filed 5-16-00; 8:45 am]
BILLING CODE 4910-13-U
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