Document ID: FAA-2008-0449-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Bell Helicopter Textron Canada Model 222, 222B, 222U, 230, and 430 Helicopters
Posted Date: 2008-04-23T04:00Z

[Federal Register: April 23, 2008 (Volume 73, Number 79)]
[Proposed Rules]               
[Page 21853-21854]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr23ap08-20]                         

[[Page 21853]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0449; Directorate Identifier 2007-SW-10-AD]
RIN 2120-AA64

 
Airworthiness Directives; Bell Helicopter Textron Canada Model 
222, 222B, 222U, 230, and 430 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes superseding an existing airworthiness 
directive (AD) for Bell Helicopter Textron Canada (Bell) Model 222, 
222B, 222U, 230, and 430 helicopters. That AD currently requires 
visually inspecting the main rotor hydraulic actuator support (support) 
to verify the presence of all dowel pins and sealant between the 
support and transmission and verifying the proper torque of each 
attaching nut (nut). This action would require the same actions as the 
existing AD but would also require the repetitive actions at intervals 
not to exceed 600 hours time-in-service (TIS) or 12 months, whichever 
occurs first. This proposal is prompted by the discovery that the 12-
month compliance requirement was correctly included in the Emergency AD 
(EAD) that we issued but was inadvertently omitted when we published 
the Final rule; request for comments following the issuance of the EAD. 
The actions specified by the proposed AD are intended to prevent 
failure of the support and subsequent loss of control of the 
helicopter.

DATES: Comments must be received on or before June 23, 2008.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    You may get the service information identified in this proposed AD 
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.
    You may examine the comments to this proposed AD in the AD docket 
on the Internet at http://www.regulations.gov.

FOR FURTHER INFORMATION CONTACT: Tyrone Millard, Aerospace Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, 
Texas 76193-0110, telephone (817) 222-5439, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to submit any written data, views, or arguments 
regarding this proposed AD. Send your comments to an address listed 
under the caption ADDRESSES. Include the docket number ``FAA-2008-0449, 
Directorate Identifier 2007-SW-10-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this proposed rulemaking. Using the 
search function of the docket Web site, you can find and read the 
comments to any of our dockets, including the name of the individual 
who sent or signed the comment. You may review the DOT's complete 
Privacy Act Statement in the Federal Register published on April 11, 
2000 (65 FR 19477-78).

Examining the Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the economic 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
in the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

Discussion

    On January 5, 2001, we issued EAD 2001-01-51 for Bell Model 222, 
222B, 222U, 230, and 430 helicopters which requires, at specified time 
intervals, visually inspecting the support for the presence of all 
dowel pins and sealant between the support and transmission and 
verifying the proper torque of each nut. That action was prompted by 
the failure of a support resulting in an accident of a Bell Model 222U 
helicopter. All retaining studs and shear pins were found sheared or 
pulled out at the junction between the support and transmission case. 
The requirements of that EAD are intended to prevent failure of the 
support and subsequent loss of control of the helicopter.
    On February 2, 2001, we issued AD 2001-01-51, Amendment 39-12105, 
Docket No. 2000-SW-54-AD as a Final rule; request for comments (66 FR 
10361, February 15, 2001). Since issuing that AD, we discovered that we 
inadvertently omitted the phrase ``or 12 months, whichever occurs 
first,'' from compliance paragraph (a) of the published final rule AD. 
Because the two versions of AD 2001-01-51 have different compliance 
times, we are proposing to supersede that AD to include the correct 
compliance time.
    The previously described unsafe condition is likely to exist or 
develop on other helicopters of these same type designs. Therefore, the 
proposed AD would supersede AD 2001-01-51 to require the following:
     Within 25 hours TIS, and thereafter at intervals not to 
exceed 600 hours TIS or 12 months, whichever occurs first:
     Visually inspect the support, part number (P/N) 222-040-
125-001, for the presence of all dowel pins and for sealant between the 
support and transmission. If any pin is missing or if no sealant is 
visible, before further flight, remove the support and further inspect 
the support, transmission case, studs, and dowel pins. Repair or 
replace any unairworthy support, transmission case, stud, or dowel pin 
before further flight.
     Verify the torque of the nuts. Upper nuts must not rotate 
at a torque less than 40 in-lbs. Lower nuts must not rotate at a torque 
less than 90 in-lbs.
     If two or more upper nuts rotate at a torque less than 40 
in-lbs. or two or more lower nuts rotate at a torque less than 90 in-
lbs., before further flight, remove the support and further inspect the 
support, transmission case, studs, and dowel pins. Repair or replace 
any unairworthy part before further flight.
     If less than two upper nuts rotate at a torque less than 
40 in-lbs. or less than two lower nuts rotate at a torque less than 90 
in-lbs., before further flight, retorque the upper nut to 50 to 70 in-

[[Page 21854]]

lbs. plus tare and the lower nut to 100 to 140 in-lbs. plus tare.
     At not less than 20 hours TIS nor more than 30 hours TIS 
after reinstalling a support for any reason, verify the torque of the 
nuts.
    We have reviewed Bell Alert Service Bulletin Nos. 222-00-86, 222U-
00-57, 230-00-18, and 430-00-17, all dated May 19, 2000 (ASB's), which 
specify, within 25 hours TIS, conducting a one-time inspection of the 
support installation by accomplishing a torque check of the support 
attaching nuts. In addition, a revision to the maintenance manual will 
introduce a recurring torque check of the nuts. Transport Canada 
classified these ASB's as mandatory and issued AD No. CF-2000-29 dated 
September 6, 2000, to ensure the continued airworthiness of these 
helicopters in Canada.
    We estimate that this proposed AD would affect 145 helicopters of 
U.S. registry. It would take approximately \1/2\ work hour per 
helicopter to inspect for proper torque, and the average labor rate is 
$80 per work hour. The cost for the inspection is estimated to be 
$5,800. Assuming 15 helicopters require removing the support for 
additional inspections, it would take approximately 6 additional work 
hours at $80 per work hour and $50 for parts at an additional total 
cost of $7,950. Based on these figures, we estimate the total cost 
impact of the proposed AD on U.S. operators to be $13,750, assuming no 
supports must be replaced.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. Additionally, this proposed 
AD 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.
    For the reasons discussed, I certify that the 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. 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.
    We prepared an economic evaluation of the estimated costs to comply 
with this proposed AD and placed it in the AD docket.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

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 39-12105 (66 FR 
10361, February 15, 2001) and by adding a new airworthiness directive 
(AD), to read as follows:

Bell Helicopter Textron Canada: Docket No. FAA-2008-0449; 
Directorate Identifier 2007-SW-10-AD. Supersedes AD 2001-01-51, 
Amendment 39-12105, Docket No. 2000-SW-54-AD.

    Applicability: Model 222, 222B, 222U, 230, and 430 helicopters, 
with a main rotor hydraulic actuator support (support), part number 
(P/N) 222-040-125-001, installed, certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent failure of the support and subsequent loss of control 
of the helicopter, accomplish the following:
    (a) Within 25 hours time-in-service (TIS) and thereafter at 
intervals not to exceed 600 hours TIS or 12 months, whichever occurs 
first, accomplish the following:
    (1) Visually inspect the support for the presence of all dowel 
pins and for sealant between the support and transmission. If any 
pin is missing, or if no sealant is visible, before further flight, 
remove the support and further inspect the support, transmission 
case, studs, and dowel pins in accordance with the Accomplishment 
Instructions, paragraphs 5 through 7, of the applicable Bell 
Helicopter Textron Alert Service Bulletin Nos. 222-00-86, 222U-00-
57, 230-00-18, or 430-00-17, all dated May 19, 2000 (ASB's). Repair 
or replace any unairworthy support, transmission case, stud, or 
dowel pin before further flight.
    (2) Verify the torque of the support attaching nuts (nuts). 
Upper nuts must not rotate at a torque less than 40 in-lbs. Lower 
nuts must not rotate at a torque less than 90 in-lbs.
    (i) If two or more upper nuts rotate at a torque less than 40 
in-lbs. or two or more lower nuts rotate at a torque less than 90 
in-lbs., before further flight, remove the support and further 
inspect the support, transmission case, studs, and dowel pins in 
accordance with the Accomplishment Instructions, paragraph 5 through 
7, of the applicable ASB's. Repair or replace any unairworthy 
support, transmission case, stud, or dowel pin before further 
flight.
    (ii) If less than two upper nuts rotate at a torque less than 40 
in-lbs. or less than two lower nuts rotate at a torque less than 90 
in-lbs., before further flight, retorque the upper nut to 50 to 70 
in-lbs. plus tare and the lower nut to 100 to 140 in-lbs. plus tare.
    (b) At not less than 20 hours TIS nor more than 30 hours TIS 
after reinstalling a support for any reason, verify the torque of 
the nuts in accordance with paragraph (a)(2) of this AD.
    (c) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Manager, Rotorcraft Standards Staff, FAA, ATTN: Tyrone 
Millard, telephone (817) 222-5439, fax (817) 222-5961, for 
information about previously approved alternative methods of 
compliance.

    Note: The subject of this AD is addressed in Transport Canada 
(Canada) AD CF-2000-29, dated September 6, 2000.

    Issued in Fort Worth, Texas, on April 14, 2008.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
 [FR Doc. E8-8754 Filed 4-22-08; 8:45 am]

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