[Federal Register Volume 68, Number 73 (Wednesday, April 16, 2003)]
[Rules and Regulations]
[Pages 18536-18538]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-9011]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-SW-01-AD; Amendment 39-13118; AD 2003-08-07]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Model 
222, 222B, 222U, and 230 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) for 
Bell Helicopter Textron Canada (BHTC) Model 222, 222B, 222U, and 230 
helicopters. This action requires inspecting the main rotor pendulum 
weight support (pendulum weight support) for file or grinding marks, 
gouges, and appropriate edge breaks. It also requires, if necessary, 
reworking and remarking or replacing the pendulum weight support. 
Regardless, this AD requires a magnetic particle inspection for a crack 
and replacing the pendulum weight support if a crack is found. This 
amendment is prompted by a pendulum weight support failure and shedding 
of the pendulum weight set in flight and a subsequent determination of 
manufacturing defects on certain serial-numbered pendulum weight 
supports. This condition, if not corrected, could result in the 
pendulum weights separating from the pendulum weight support and 
striking the vertical fin or tail rotor, and subsequent loss of control 
of the helicopter.

DATES: Effective May 1, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 1, 2003.

[[Page 18537]]

    Comments for inclusion in the Rules Docket must be received on or 
before June 16, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2003-SW-01-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 service information referenced in this AD 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. 
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: Charles Harrison, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort 
Worth, Texas 76193-0110, telephone (817) 222-5128, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: Transport Canada, which is the airworthiness 
authority for Canada, notified the FAA that an unsafe condition may 
exist on BHTC Model 222, 222B, 222U, and 230 helicopters. Transport 
Canada advises that pendulum weight supports could have manufacturing 
discrepancies like file or grinding marks, gouges, or too small edge 
radius. This part, if not reworked and inspected or replaced, could 
fail in flight.
    BHTC has issued the following alert service bulletins, all dated 
March 28, 2002:
    [sbull] Bell Helicopter Textron (BHT) Alert Service Bulletin (ASB) 
222-02-92 for Model 222 and 222B helicopters;
    [sbull] BHT ASB 222U-02-63 for Model 222U helicopters; and
    [sbull] BHT ASB 230-02-25 for Model 230 helicopters.
The ASBs specify inspecting the pendulum support weights and, if 
necessary, reworking and remarking or replacing the pendulum weight 
supports no later than the next scheduled 150 hours time-in-service 
(TIS) inspection, and prior to installation of spare supports. 
Transport Canada classified these ASBs as mandatory and issued AD CF-
2002-33, dated July 4, 2002, to ensure the continued airworthiness of 
these helicopters in Canada. Transport Canada's AD requires 
accomplishing the actions within 50 hours TIS, as does this AD.
    These helicopter models are manufactured in Canada and are type 
certificated for operation in the United States under the provisions of 
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the 
applicable bilateral agreement, Transport Canada has kept the FAA 
informed of the situation described above. The FAA has examined the 
findings of Transport Canada, reviewed all available information, and 
determined that AD action is necessary for products of these type 
designs that are certificated for operation in the United States.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type designs registered in the United States. 
Therefore, this AD is being issued to prevent the pendulum weights from 
separating and striking the vertical fin or tail rotor, and subsequent 
loss of control of the helicopter. This AD requires, within 50 hours 
TIS, inspecting each pendulum weight support, part number (P/N) 222-
011-114-101 or ``103, for file or grinding marks, gouges, and 
appropriate edge breaks. It also requires, if necessary, reworking and 
remarking or replacing the pendulum weight support. Regardless, this AD 
requires a magnetic particle inspection for a crack and replacing the 
pendulum weight support if a crack is found. The actions must be 
accomplished in accordance with the ASB's described previously. The 
short compliance time involved is required because the previously 
described critical unsafe condition can adversely affect the 
controllability or structural integrity of the helicopter. Therefore, 
inspecting each pendulum weight support for discrepancies, reworking 
and remarking or replacing each pendulum weight support, if necessary, 
and performing a magnetic particle inspection for a crack (and 
replacing the pendulum weight support if a crack is found) is required 
within 50 hours TIS, 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 108 helicopters will be affected by this AD, 
that it will take approximately 10 work hours to accomplish the 
inspection, reworking and remarking or replacing the two pendulum 
weight supports, and that the average labor rate is $60 per work hour. 
Required parts will cost approximately $1,734 per helicopter. Based on 
these figures, the total cost impact of the AD on U.S. operators is 
estimated to be $252,072, assuming that all helicopters in the fleet 
will require replacing two pendulum weight supports.

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. 2003-SW-01-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

[[Page 18538]]

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

0
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

0
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]

0
2. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2003-08-07 Bell Helicopter Textron Canada: Amendment 39-13118. 
Docket No. 2003-SW-01-AD.

    Applicability: Model 222 helicopters, serial numbers (S/N) 47006 
through 47089; Model 222B helicopters, S/N 47131 through 47156; 
Model 222U helicopters, S/N 47501 through 47574; and Model 230 
helicopters, S/N 23001 through 23038, with main rotor pendulum 
weight support (pendulum weight support), part number (P/N) 222-011-
114-101 or -103, except for pendulum weight supports with a S/N 
having a prefix of ``FN'' and numbers 363 through 409, 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 (f) 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 within 50 hours time-in-service, unless 
accomplished previously.
    To prevent the main rotor pendulum weights (pendulum weights) from 
separating from the pendulum weight support and striking the vertical 
fin or tail rotor, and subsequent loss of control of the helicopter, 
accomplish the following:
    (a) Inspect the edges of each pendulum weight support, P/N 222-011-
114-101 or -103, for an edge break of 0.02 to 0.04 inch radius or 0.02 
to 0.04 inch x 45 degrees chamfer in accordance with the Accomplishment 
Instructions, paragraphs 1 through 3, in Bell Helicopter Textron (BHT) 
Alert Service Bulletin (ASB) 222-02-92 for Model 222 and 222B 
helicopters; BHT ASB 222U-02-63 for Model 222U helicopters; or BHT ASB 
230-02-25 for Model 230 helicopters, all dated March 28, 2002.
    (b) Inspect the edges of each pendulum weight support for file 
marks, grinding marks, or gouges, and to ensure that edge break 
machining/polishing marks are in the correct direction as shown in 
Figure 1 of each ASB cited in paragraph (a) of this AD.
    (c) If the edge breaks do not meet the requirements in paragraphs 
(a) and (b) of this AD:
    (1) Rework the edges in accordance with Figure 1 and the 
Accomplishment Instructions, paragraph 6, in the applicable ASB.
    (2) Perform a magnetic particle inspection of the pendulum weight 
supports for a crack.
    (3) Re-identify reworked pendulum weight supports in accordance 
with the Accomplishment Instructions, paragraphs 8 through 10, in the 
applicable ASB.
    (d) If the edge breaks meet the requirements in paragraphs (a) and 
(b) of this AD, perform a magnetic particle inspection of the pendulum 
weight supports for a crack.
    (e) If a crack is found in the pendulum weight support or the 
pendulum weight support cannot be reworked to meet the requirements of 
this AD, replace the pendulum weight support with an airworthy pendulum 
weight support before further flight.
    (f) 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.

    (g) 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.
    (h) The inspections and rework and replacement, if necessary, shall 
be done in accordance with Bell Helicopter Textron Alert Service 
Bulletin 222-02-92, Bell Helicopter Textron Alert Service Bulletin 
222U-02-63, or Bell Helicopter Textron Alert Service Bulletin 230-02-
25, all dated March 28, 2002. 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. 
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.
    (i) This amendment becomes effective on May 1, 2003.

    Note 3: The subject of this AD is addressed in Transport Canada 
(Canada) AD CF-2002-33, dated July 4, 2002.


    Issued in Fort Worth, Texas, on April 7, 2003.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 03-9011 Filed 4-15-03; 8:45 am]
BILLING CODE 4910-13-P