[Federal Register Volume 79, Number 29 (Wednesday, February 12, 2014)]
[Proposed Rules]
[Pages 8358-8360]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-02954]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0070; Directorate Identifier 2011-SW-062-AD]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
Bell Helicopter Textron Canada (BHTC) Model 407 helicopters. This 
proposed AD would require 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 would require 
replacing or repairing a part or section, depending on the inspection's 
outcome. This proposed AD is prompted by reports of cracks in the upper 
left-hand longeron. The proposed 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: We must receive comments on this proposed AD by April 14, 2014.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

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 proposed AD, the foreign 
authority's 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.
    For service information identified in this proposed 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.

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: 

Comments Invited

    We invite you to participate in this rulemaking by submitting 
written comments, data, or views. We also invite comments relating to 
the economic, environmental, energy, or federalism impacts that might 
result from adopting the proposals in this document. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. To 
ensure the docket does not contain duplicate comments, commenters 
should send only one copy of written comments, or if comments are filed 
electronically, commenters should submit only one time.
    We will file in the docket all comments that we receive, as well as 
a report summarizing each substantive public contact with FAA personnel 
concerning this proposed rulemaking. Before acting on this proposal, we 
will consider all comments we receive on or before the closing date for 
comments. We will consider comments filed after the comment period has 
closed if it is possible to do so without incurring expense or delay. 
We may change this proposal in light of the comments we receive.

Discussion

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian AD No. CF-2011-42, dated 
November 9, 2011, to correct an unsafe condition for certain BHTC Model 
407 helicopters. TCCA advises that longeron assemblies, part numbers 
(P/Ns) 206-031-314-037, 206-031-314-177, and 206-031-314-219B, 
installed on helicopters with

[[Page 8359]]

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. 
The TCCA AD also requires 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 of the TCCA AD.

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, the TCCA, its technical 
representative, has notified us of the unsafe condition described in 
its AD. We are proposing this AD because we evaluated all known 
relevant information and determined that an unsafe condition is likely 
to exist or develop on other products of the same type design.

Related Service Information

    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.

Proposed AD Requirements

    We propose the following:
    Within 50 hours time-in-service (TIS), or prior to reaching 1,250 
hours TIS since new, whichever occurs later, visually inspect the upper 
skin for a crack using a 10X or higher power magnifying glass.
     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. If there are no cracks, 
corrosion, or other damage in the longeron assembly, before further 
flight, replace the upper skin with an airworthy upper skin. Repeat the 
inspection of the longeron assembly at intervals not to exceed 50 hours 
TIS. If there is a crack, corrosion, or other damage in the longeron 
assembly, before further flight: Repair the longeron assembly or 
replace it with an airworthy longeron assembly, P/N 206-031-314-237B, 
and reinstall the upper skin or replace it with an airworthy upper 
skin. Install three external strap doublers. Repeat the inspection of 
the longeron assembly at intervals not to exceed 50 hours TIS.
     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. If there is a 
crack, corrosion, or other damage in the longeron assembly, before 
further flight: Repair the longeron assembly or replace it with an 
airworthy longeron assembly, P/N 206-031-314-237B. Install three 
external strap doublers. Repeat the inspection of the upper skin and 
longeron assembly at intervals not to exceed 50 hours TIS. 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.
     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. If there is no crack in the 
upper skin and no crack, corrosion or other damage in the longeron 
assembly, you may install three external strap doublers, which will 
extend the recurring 50 hours TIS inspection interval to 150 hours TIS.

Costs of Compliance

    We estimate that this proposed AD would affect 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 would 
require 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 would require 3 work hours for a labor cost of $255 per 
helicopter. Parts would cost $723 for parts for total cost of $978 per 
helicopter.
    Repairing the longeron if needed and installing the doublers would 
require 16 work hours for a labor cost of $1,360. Parts would 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 would require 24 work 
hours for a labor cost of $2,040. Parts would 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 products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. 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 this 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);
    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,

[[Page 8360]]

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.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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):

Bell Helicopter Textron Canada: 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) Comments Due Date

    We must receive comments by April 14, 2014.

(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 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 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 in the AD docket on the Internet at http://www.regulations.gov.

(h) Subject

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

    Issued in Fort Worth, Texas, on January 31, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-02954 Filed 2-11-14; 8:45 am]
BILLING CODE 4910-13-P