[Federal Register Volume 80, Number 50 (Monday, March 16, 2015)]
[Rules and Regulations]
[Pages 13481-13483]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-05571]



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  Federal Register / Vol. 80, No. 50 / Monday, March 16, 2015 / Rules 
and Regulations  

[[Page 13481]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0070; Directorate Identifier 2011-SW-062-AD; 
Amendment 39-18114; AD 2015-05-04]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for Bell 
Helicopter Textron Canada (BHTC) Model 407 helicopters. This AD 
requires inspecting the aft fuselage upper skin (upper skin) for a 
crack and the upper left longeron assembly (longeron assembly) for a 
crack, corrosion, or defect. This AD requires replacing or repairing a 
part or section, depending on the inspection's outcome. This AD was 
prompted by reports of cracks in the upper left-hand longeron. This 
AD's actions are intended to prevent failure of the longeron assembly 
or the upper skin, which could lead to a structural failure and loss of 
helicopter control.

DATES: This AD is effective April 20, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of April 20, 2015.

ADDRESSES: For service information identified in this AD, contact Bell 
Helicopter Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel, 
Quebec J7J1R4; telephone (450) 437-2862 or (800) 363-8023; fax (450) 
433-0272; or at http://www.bellcustomer.com/files/. You may review the 
referenced service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas 76137. It is also available on the Internet at http://www.regulations.gov by searching and locating Docket No. FAA 2014-0070.

Examining the AD 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 AD, the Transport Canada Civil 
Aviation (TCCA) AD, any incorporated-by-reference service information, 
the economic evaluation, any comments received, and other information. 
The street address for the Docket Operations Office (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations Office, 
M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue 
SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; 
email [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    On February 12, 2014, at 79 FR 8358, the Federal Register published 
our notice of proposed rulemaking (NPRM), which proposed to amend 14 
CFR part 39 by adding an AD that would apply to BHTC Model 407 
helicopters, with a serial number 53000 through 53900, 53911 through 
54061, and 54300, with longeron assembly, part number (P/N) 206-031-
314-037, 206-031-314-177, or 206-031-314-219B. The NPRM proposed to 
require inspecting the upper skin for a crack and longeron assembly for 
a crack, corrosion, or defect. The NPRM also proposed to require 
replacing or repairing a part or section, depending on the inspection's 
outcome. The proposed requirements were intended to prevent failure of 
the longeron assembly or the upper skin, which could lead to a 
structural failure and loss of helicopter control.
    The NPRM was prompted by Canadian AD No. CF-2011-42, dated November 
9, 2011, issued by TCCA, which is the aviation authority for Canada, to 
correct an unsafe condition for certain BHTC Model 407 helicopters. 
TCCA advises that longeron assemblies, P/Ns 206-031-314-037, 206-031-
314-177, and 206-031-314-219B, installed on helicopters with 1,200 or 
more hours air time, are prone to cracking. The TCCA AD requires, based 
on hours air time since new, visually inspecting the aft fuselage upper 
skin for cracks and replacing the skin if cracked and visually 
inspecting the longeron assembly for cracks and general condition. If 
the longeron assembly is serviceable, the TCCA AD requires repeating 
the inspection of the longeron assembly for cracks and general 
condition at intervals based on whether external strap doublers are 
installed. If the longeron assembly is cracked, the TCCA AD requires 
repairing or replacing it, installing three external strap doublers, 
and repeating the inspection of the longeron assembly if it was 
repaired. Installing a new longeron assembly, P/N 206-031-314-237B, and 
the three external strap doublers constitutes terminating action for 
the requirements of the TCCA AD.

Comments

    After our NPRM (79 FR 8358, February 12, 2014) was published, we 
received comments from one commenter.

Request

    A BHTC representative requested that we change the AD to be 
consistent with the requirements in the TCCA AD and the Bell service 
information. The commenter stated that the NPRM's inspection intervals 
were more restrictive with no additional safety benefit. According to 
the commenter, the NPRM proposed an inspection interval of 50 hours 
whenever the strap doublers but not new longeron are installed, while 
the TCCA AD and service information increased the inspection interval 
to 150 hours. Also, the commenter stated the NPRM increased the 
inspection interval to 150 hours when a new longeron is installed with 
the strap doublers, while the TCCA AD and service information provide 
this as terminating action.
    We disagree. Although they are arranged and worded differently, the 
actions proposed in the NPRM are the same as those in the TCCA AD and 
service information. Paragraph (e)(4) of the Required Actions extends 
the inspection interval to 150 hours when

[[Page 13482]]

the strap doublers are installed without the new longeron. Paragraph 
(e)(3) of the Required Actions states that replacing the longeron 
assembly with a new longeron assembly and installing three external 
strap doublers constitutes terminating action to the requirements of 
the AD. This is consistent with the TCCA AD and the BHTC service 
information.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
Canada and are approved for operation in the United States. Pursuant to 
our bilateral agreement with Canada, TCCA, its technical 
representative, has notified us of the unsafe condition described in 
the TCCA AD. We are issuing this AD because we evaluated all 
information provided by TCCA and determined the unsafe condition exists 
and is likely to exist or develop on other helicopters of these same 
type designs and that air safety and the public interest require 
adopting the AD requirements as proposed.

Related Service Information Under 1 CFR Part 51

    BHTC has issued Alert Service Bulletin 407-11-95, Revision C, dated 
April 20, 2012 (ASB), to correct an unsafe condition for Model 407 
helicopters, serial numbers 53000 through 53900, 53911 through 54061, 
and 54300, with a flight time of 1200 or more hours, and with a 
longeron assembly, P/N 206-031-314-037, 206-031-314-177, or 206-031-
314-219B. The ASB states that BHTC received reports of longeron 
assemblies cracking in service. The ASB:
     Specifies a one-time inspection of the aft fuselage top 
skin and repetitive inspections of the upper left longeron assembly;
     Provides a repair procedure for the longeron assembly;
     Allows for the installation of longeron assembly, P/N 206-
031-314-237B, and three external strap doublers as terminating action 
for the repetitive inspection requirements.
    This service information is reasonably available; see ADDRESSES for 
ways to access this service information.

Costs of Compliance

    We estimate that this AD affects 584 helicopters of U.S. Registry 
and that labor costs average $85 an hour. Based on these estimates, we 
estimate the following costs:
     A one-time visual inspection of the aft fuselage upper 
skin requires 1 work-hour and no parts for a total cost of $85 per 
helicopter, $49,640 for the U.S. fleet.
     A visual inspection of the longeron and replacing the aft 
fuselage upper skin requires 3 work hours for a labor cost of $255 per 
helicopter. Parts cost $723 for total cost of $978 per helicopter.
     Repairing the longeron if needed and installing the 
doublers requires 16 work hours for a labor cost of $1,360. Parts cost 
$3,928 for a total cost of $5,288 per helicopter.
     Replacing the longeron with P/N 206-031-314-237B combined 
with the installation of the three external strap doublers require 24 
work hours for a labor cost of $2,040. Parts cost $13,560 for a total 
cost of $15,600 per helicopter.

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 helicopters identified in this 
rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD 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.
    For the reasons discussed above, I certify that this AD:
    (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);
    (3) Will not affect intrastate aviation in Alaska to the extent 
that it justifies making a regulatory distinction; and
    (4) 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 AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2015-05-04 Bell Helicopter Textron Canada Helicopters: Amendment 39-
18114; Docket No. FAA-2014-0070; Directorate Identifier 2011-SW-062-
AD.

(a) Applicability

    This AD applies to Bell Helicopter Textron Canada (BHTC) Model 
407 helicopters, with a serial number 53000 through 53900, 53911 
through 54061, and 54300, with an upper left longeron assembly 
(longeron assembly), part number (P/N) 206-031-314-037, 206-031-314-
177, or 206-031-314-219B, installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in the aft 
fuselage upper skin or a crack, corrosion, or defect in the longeron 
assembly. This condition could cause structural failure and 
consequently, loss of helicopter control.

(c) Effective Date

    This AD becomes effective April 20, 2015.

(d) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

(e) Required Actions

    Within 50 hours time-in-service (TIS), or prior to reaching 
1,250 hours TIS since new, whichever occurs later, visually inspect 
the helicopter's aft fuselage upper skin (upper skin) for a crack 
using a 10X or higher power magnifying glass.
    (1) If there is a crack in the upper skin, before further 
flight, remove the skin and inspect the longeron assembly, paying 
attention to the upper flange, for a crack, corrosion, or other 
damage using a 10X or higher power magnifying glass.
    (i) If there are no cracks, corrosion, or other damage in the 
longeron assembly, before further flight, replace the upper skin 
with an

[[Page 13483]]

airworthy upper skin. Repeat the inspection of the longeron assembly 
at intervals not to exceed 50 hours TIS.
    (ii) If there is a crack, corrosion, or other damage in the 
longeron assembly, before further flight:
    (A) Repair the longeron assembly or replace it with an airworthy 
longeron assembly, part number (P/N) 206-031-314-237B, and reinstall 
the upper skin or replace it with an airworthy upper skin.
    (B) Install three external strap doublers in accordance with 
Part III, paragraphs 5 through10 of Bell Helicopter Alert Service 
Bulletin 407-11-95, Revision C, dated April 20, 2012 (ASB).
    (C) Repeat the inspection of the longeron assembly at intervals 
not to exceed 50 hours TIS.
    (2) If there is no crack in the upper skin, within 10 hours TIS, 
visually inspect the longeron assembly using a 10X or higher power 
magnifying glass for a crack, corrosion, or other damage.
    (i) If there is a crack, corrosion, or other damage in the 
longeron assembly, before further flight:
    (A) Repair the longeron assembly or replace it with an airworthy 
longeron assembly, P/N 206-031-314-237B.
    (B) Install three external strap doublers in accordance with 
Part III, paragraphs 5 through 10 of the ASB.
    (C) Repeat the inspection of the upper skin and longeron 
assembly at intervals not to exceed 50 hours TIS.
    (ii) If there are no cracks, corrosion, or other damage in the 
longeron assembly, repeat the inspection of the upper skin and 
longeron assembly at intervals not to exceed 50 hours TIS.
    (3) Replacing the longeron assembly with longeron assembly, P/N 
206-031-314-237B, and installing three external strap doublers 
constitutes terminating action for this AD.
    (4) If there is no crack in the upper skin and there is no 
crack, corrosion, or other damage in the longeron assembly, you may 
install three external strap doublers in accordance with Part III, 
paragraphs 5 through 10 of the ASB. This option extends the 
recurring 50 hours TIS inspection interval to 150 hours TIS.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Sharon Miles, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-
5110; email [email protected].
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, we suggest that you 
notify your principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office or 
certificate holding district office, before operating any aircraft 
complying with this AD through an AMOC.

(g) Additional Information

    The subject of this AD is addressed in Transport Canada Civil 
Aviation (TCCA) AD No. CF-2011-42, dated November 9, 2011. You may 
view the TCCA AD on the Internet at http://www.regulations.gov in 
Docket No. FAA-2014-0070.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 5313, Fuselage 
Main, Longeron/Stringer.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Bell Helicopter Alert Service Bulletin 407-11-95, Revision 
C, dated April 20, 2012.
    (ii) Reserved.
    (3) For BHTC service information identified in this AD, contact 
Bell Helicopter Textron Canada Limited, 12,800 Rue de l'Avenir, 
Mirabel, Quebec J7J1R4; telephone (450) 437-2862 or (800) 363-8023; 
fax (450) 433-0272; or at http://www.bellcustomer .com/files/.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137. For information on the availability of this 
material at the FAA, call (817) 222-5110.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on March 3, 2015.
Bruce E. Cain,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-05571 Filed 3-13-15; 8:45 am]
 BILLING CODE 4910-13-P