[Federal Register Volume 66, Number 184 (Friday, September 21, 2001)]
[Rules and Regulations]
[Pages 48535-48538]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-23416]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-29-AD; Amendment 39-12443; AD 2001-13-51]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Model 
206L-4, 407, and 427 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment 
adopting Airworthiness Directive (AD)

[[Page 48536]]

2001-13-51, which was sent previously to all known U.S. owners and 
operators of Bell Helicopter Textron Canada (BHTC) Model 206L-4, 407, 
and 427 helicopters by individual letters. This AD requires visually 
inspecting certain driveshafts for a crack, a loose bolt or nut, or red 
powder residue. If a crack, a loose bolt or nut, or red powder residue 
is found, replacing the driveshaft before further flight and notifying 
the FAA within 10 days is also required. This amendment is prompted by 
a driveshaft failure on a BHTC Model 407 helicopter that resulted in an 
engine shutdown and an emergency landing. Failure of the driveshaft was 
due to cracking of the flexframe on the forward end of the driveshaft. 
In addition, three other incidents of a cracked flexframe on the 
forward end of the driveshaft on other Model 407 helicopters have been 
reported. The actions specified by this AD are intended to prevent 
failure of a driveshaft, loss of drive to the main rotor system, and a 
subsequent emergency forced landing.

DATES: Effective October 9, 2001, to all persons except those persons 
to whom it was made immediately effective by Emergency AD 2001-13-51, 
issued on June 27, 2001, which contained the requirements of this 
amendment.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 9, 2001. Comments for inclusion in the Rules Docket must be 
received on or before November 20, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2001-SW-29-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].
    The applicable service information may be obtained from Bell 
Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, Quebec 
J7J1R4, telephone (450) 437-2862 or (800) 363-8023, fax (450) 433-0272. 
The service information may also be obtained by e-mailing a request to 
[email protected]. 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: Paul Madej, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, 
Texas 76193-0110, telephone (817) 222-5125, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: On June 27, 2001, the FAA issued Emergency 
AD 2001-13-51 for BHTC Model 206L-4, 407, and 427 helicopters, which 
requires the following if driveshaft, part number 206-340-300-105, has 
ever been installed on a BHTC Model 407 helicopter:
     At specified hours time-in-service (TIS), visually inspect 
each driveshaft for a crack, a loose bolt or nut, or red powder 
residue.
     Before further flight, replace the driveshaft with an 
airworthy driveshaft if a crack, a loose bolt or nut, or red powder 
residue is found. Within 10 days, notify the Manager, Regulations 
Group, FAA, of the helicopter serial number, driveshaft serial number, 
and driveshaft hours TIS.
     After the effective date of this AD, interchanging a 
driveshaft between different helicopter models is prohibited if that 
driveshaft has ever been installed on a BHTC Model 407 helicopter.

That action was prompted by a driveshaft failure on a BHTC Model 407 
helicopter that resulted in an engine shutdown and an emergency 
landing. Failure of the driveshaft was due to cracking of the flexframe 
on the forward end of the driveshaft. The BHTC Model 206L-4 and 427 
helicopters use the same part-numbered driveshaft. In addition, three 
other incidents of a cracked flexframe on the forward end of the 
driveshaft on other Model 407 helicopters have been reported. This 
condition, if not detected, could result in failure of a driveshaft, 
loss of drive to the main rotor system, and a subsequent emergency 
forced landing.
    Transport Canada, which is the airworthiness authority for Canada, 
notified the FAA that an unsafe condition may exist on BHTC Model 407 
helicopters. Transport Canada advises that during flight the 
driveshaft, P/N 206-340-300-105, failed causing engine shutdown and a 
forced landing. Three other incidents of the cracked flexframe on the 
forward end of the BHTC Model 407 driveshafts were also reported. 
Pending further corrective action, Transport Canada determined that a 
one-time visual inspection for any obvious discrepancy of the 
driveshaft is warranted.
    The FAA has reviewed BHTC Alert Service Bulletin No. 407-01-43, 
dated June 8, 2001 (ASB), which describes procedures for a one-time 
inspection of the engine-to-transmission driveshaft, P/N 206-340-300-
105. Transport Canada classified this ASB as mandatory and issued AD 
CF-2001-24, dated June 11, 2001, to ensure the continued airworthiness 
of BHTC Model 407 helicopters in Canada.
    Since the unsafe condition described is likely to exist or develop 
on other BHTC Model 206L-4, 407, and 427 helicopters of the same type 
designs, the FAA issued Emergency AD 2001-13-51 to prevent failure of a 
driveshaft, loss of drive to the main rotor system, and a subsequent 
emergency forced landing. The AD requires the actions specified above. 
The inspections must 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 and controllability of the 
helicopter. Therefore, visually inspecting the driveshaft at the 
specified time intervals and replacing the driveshaft, if necessary, is 
required before further flight, and this AD must be issued immediately.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment thereon were 
impracticable and contrary to the public interest, and good cause 
existed to make the AD effective immediately by individual letters 
issued on June 27, 2001 to all known U.S. owners and operators of BHTC 
Model 206L-4, 407, and 427 helicopters. These conditions still exist, 
and the AD is hereby published in the Federal Register as an amendment 
to 14 CFR 39.13 to make it effective to all persons. However, a few 
editorial changes have been made to the AD. The zip code listed for the 
manufacturer has been corrected and an e-mail address for obtaining 
service information has been added. Also, due to confusion expressed by 
an operator, paragraph (a)(1)(i) has been changed to clarify that the 
notification requirement is necessary only if a crack, a loose bolt or 
nut, or red powder residue is found during the visual inspection. The 
FAA has determined that these changes will neither increase the 
economic burden on an operator nor increase the scope of the AD
    The FAA estimates that 488 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately 4 work hours per 
helicopter to visually inspect the driveshaft. The average labor rate 
is $60 per work hour. Based on these figures, the total cost impact of 
the AD on U.S. operators is estimated to be $117,120, assuming that 
each driveshaft is inspected once.

[[Page 48537]]

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 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 mailed 
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. 2001-SW-29-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 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:

2001-13-51  Bell Helicopter Textron Canada: Amendment 39-12443. 
Docket No. 2001-SW-29-AD.

    Applicability: Model 206L-4, 407, and 427 helicopters, with 
engine-to-transmission driveshaft assembly (driveshaft), part number 
206-340-300-105, 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 (c) 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 failure of a driveshaft, loss of drive to the main 
rotor system, and a subsequent emergency forced landing, accomplish 
the following:
    (a) If a driveshaft has ever been installed on a Bell Helicopter 
Textron Canada (BHTC) Model 407 helicopter, within 25 hours time-in-
service (TIS) for driveshafts with 1000 or more hours TIS and for 
driveshafts with 1000 or less hours TIS that have been removed or 
installed since helicopter delivery, and within 300 hours TIS for 
driveshafts with less than 1000 hours TIS that have never been 
removed or installed since helicopter delivery:
    (1) Visually inspect each driveshaft for a crack, loose bolt or 
nut, or red powder residue, in accordance with the Accomplishment 
Instructions, paragraphs 1 through 7 of Bell Helicopter Textron 
Alert Service Bulletin 407-01-43, dated June 8, 2001 (ASB).
    (2) Before further flight, if a crack, a loose bolt or nut, or 
red powder residue is found, replace the driveshaft with an 
airworthy driveshaft.
    (i) If a crack, a loose bolt or nut, or red powder residue is 
found, notify the Manager, Regulations Group, FAA, Rotorcraft 
Directorate, Fort Worth, Texas 76193-0111, of the helicopter serial 
number, driveshaft serial number, and driveshaft hours TIS within 10 
days.
    (ii) Reporting requirements have been approved by the Office of 
Management and Budget and assigned OMB control number 2120-0056.
    (b) After the effective date of this AD, interchanging a 
driveshaft between different helicopter models is prohibited if that 
driveshaft has ever been installed on a BHTC Model 407 helicopter.
    (c) 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 Manager, Regulations Group.

    (d) Special flight permits may be issued in accordance with 14 
CFR 21.197 and 21.199 to operate the helicopter to a location where 
the requirements of this AD can be accomplished.
    (e) The visual inspection shall be done in accordance with the 
Accomplishment Instructions, paragraphs 1 through 7 of Bell 
Helicopter Textron Alert Service Bulletin 407-01-43, dated June 8, 
2001. 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 J7J1R4, telephone (450) 437-
2862 or (800) 363-8023, fax (450) 433-0272, or by e-mailing a 
request to [email protected]. 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.
    (f) This amendment becomes effective on October 9, 2001, to all 
persons except those persons to whom it was made immediately 
effective by Emergency AD 2001-13-51, issued June 27, 2001, which 
contained the requirements of this amendment.


[[Page 48538]]


    Note 3: The subject of this AD is addressed in Transport Canada 
(Canada) AD CF-2001-24, dated June 11, 2001.


    Issued in Fort Worth, Texas, on September 12, 2001.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 01-23416 Filed 9-20-01; 8:45 am]
BILLING CODE 4910-13-P