[Federal Register Volume 65, Number 143 (Tuesday, July 25, 2000)]
[Rules and Regulations]
[Pages 45703-45704]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-18521]



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  Federal Register / Vol. 65, No. 143 / Tuesday, July 25, 2000 / Rules 
and Regulations  

[[Page 45703]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-SW-10-AD; Amendment 39-11827; AD 2000-14-16]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Model 
407 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD) for Bell Helicopter Textron Canada (BHTC) Model 407 helicopters. 
That AD 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 AD requires 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 AD 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 this 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: Effective August 29, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 29, 2000.

ADDRESSES: The service information referenced in this AD may be 
obtained from Bell Helicopter Textron Canada, 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; or at the Office of the Federal Register, 800 North Capitol 
Street, NW., suite 700, Washington, DC.

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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 99-06-15, 
Amendment 39-11111 (64 FR 16801, April 7, 1999), which applies to BHTC 
Model 407 helicopters, was published in the Federal Register on May 17, 
2000 (65 FR 31291). That action proposed to require installing a 
redesigned tail rotor system, modifying the vertical fin and horizontal 
stabilizer, and restoring the Vne to 140 knots IAS.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed except for removing unnecessary 
wording from the introductory unsafe condition paragraph and removing 
the superseded AD number from Figure 1.
    The FAA estimates that 200 helicopters of U.S. registry will be 
affected by this AD. It will take approximately 80 work hours per 
helicopter to perform the modifications and installations and the 
average labor rate is $60 per work hour. Required parts will 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 AD on U.S. 
operators is estimated to be $5,792,200 or $28,961 per helicopter, 
assuming no costs are reimbursed.
    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.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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 39-11111 (64 FR 
16801), and by adding a new airworthiness directive (AD), Amendment 39-
11827, to read as follows:

2000-14-16  Bell Helicopter Textron Canada: Amendment 39-11827. 
Docket No. 2000-SW-10-AD. Supersedes AD 99-06-15, Amendment 39-
11111, Docket No. 99-SW-16-AD.


[[Page 45704]]


    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, 
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.

                                                      Figure 1.--407 Airspeed Limitations-Knots-IAS
--------------------------------------------------------------------------------------------------------------------------------------------------------
              OAT                                                              Pressure altitude FT X 1000
--------------------------------------------------------------------------------------------------------------------------------------------------------
             C deg.                  0          2          4          6          8          10         12         14         16         18         20
--------------------------------------------------------------------------------------------------------------------------------------------------------
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
--------------------------------------------------------------------------------------------------------------------------------------------------------

    (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 
sections 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.
    (f) The modifications shall be done in accordance with Parts I 
and II of the Accomplishment Instructions in Bell Helicopter Textron 
Canada Technical Bulletin 407-98-13, dated December 12, 1998; Part 
II of Bell Helicopter Textron Technical Bulletin 407-99-17, dated 
April 15, 1999; Bell Helicopter Textron Technical Bulletin No. 407-
96-2, Revision A, dated March 11, 1997; and Parts I, II, and III of 
Bell Helicopter Textron Alert Service Bulletin 407-99-33, Revision 
A, dated March 10, 2000. 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 Bell 
Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, Quebec 
JON1LO, telephone (800) 463-3036, fax (514) 433-0272. 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 August 29, 2000.

    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 July 12, 2000.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-18521 Filed 7-24-00; 8:45 am]
BILLING CODE 4910-13-U