Document ID: FAA-2018-0866-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Bell Helicopter Textron Inc. Helicopters
Posted Date: 2019-04-11T04:00Z

[Federal Register Volume 84, Number 70 (Thursday, April 11, 2019)]
[Proposed Rules]
[Pages 14626-14628]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-07176]

 ========================================================================
 Proposed Rules
                                                 Federal Register
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
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  Federal Register / Vol. 84, No. 70 / Thursday, April 11, 2019 / 
Proposed Rules  

[[Page 14626]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0866; Product Identifier 2018-SW-083-AD]
RIN 2120-AA64

Airworthiness Directives; Bell Helicopter Textron Inc. 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede airworthiness directive (AD) 2011-12-
08 for Bell Helicopter Textron Inc. (Bell) Model 205A, 205A-1, 205B, 
212, 412, 412CF, and 412EP helicopters. AD 2011-12-08 requires a one-
time inspection of the tail rotor (T/R) blade for corrosion and 
pitting. Since we issued AD 2011-12-08, Bell has implemented new 
manufacturing and inspection procedures that correct the unsafe 
condition on more recently manufactured T/R blades. This proposed AD 
would retain the requirements of AD 2011-12-08 while excluding certain 
T/R blades from the applicability. The actions of this proposed AD are 
intended to address an unsafe condition on these products.

DATES: We must receive comments on this proposed AD by June 10, 2019.

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 by searching for and locating Docket No. FAA-2018-
0866; or in person at Docket Operations 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 Docket Operations (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 rule, contact 
Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; 
telephone (817) 280-3391; fax (817) 280-6466; or at http://www.bellcustomer.com/files/. You may review service information at the 
FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood 
Pkwy., Room 6N-321, Fort Worth, TX 76177.

FOR FURTHER INFORMATION CONTACT: Daniel Moore, Aviation Safety 
Engineer, DSCO Branch, Compliance and Airworthiness Division, FAA, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5418; 
email da[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

    We issued AD 2011-12-08, Amendment 39-16715 (76 FR 35334, June 17, 
2011) (AD 2011-12-08) for Bell Model 205A, 205A-1, 205B, 212, 412, 
412CF, and 412EP helicopters with a T/R blade, part number 212-010-750 
(all dash numbers), all serial numbers (S/Ns) except those with a 
prefix of ``A'' and the number 17061 or larger. AD 2011-12-08 requires 
a one-time inspection of the T/R blade for corrosion and pitting after 
sanding the paint from the spar area between blade stations 22.5 and 
40.0, and repairing or replacing the T/R blade if corrosion or pitting 
is discovered. AD 2011-12-08 was prompted by a report from Bell that T/
R blades with certain S/Ns may have manufacturing anomalies, identified 
as pits or corrosion, in the spar area as a result of the chemical 
milling process. The actions in AD 2011-12-08 are intended to detect 
corrosion or pitting in the forward spar area of a T/R blade to prevent 
a crack in the T/R blade, loss of the T/R blade, and subsequent loss of 
helicopter control.

Actions Since AD 2011-12-08 Was Issued

    Since we issued AD 2011-12-08, Bell has implemented new 
manufacturing and inspection procedures for its T/R blades. These 
recently-manufactured T/R blades have a prefix of ``BH'' before the S/N 
and are not subject to the unsafe condition. Therefore, we propose to 
supersede AD 2011-12-08 to remove these blades from the applicability 
of the AD. This proposed AD would not change the inspection 
requirements.
    Additionally, since AD 2011-12-08 was issued, the FAA's Aircraft 
Certification Service has changed its organization structure. The new 
structure replaces product directorates with functional divisions. We 
have revised some of the office titles and nomenclature throughout this 
proposed AD to reflect the new organizational changes. Information 
about the new structure can be found in the Notice

[[Page 14627]]

published on July 25, 2017 (82 FR 34564).

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
still likely to exist or develop in other products of these same type 
designs.

Related Service Information Under 1 CFR Part 51

    We have reviewed the following Bell Alert Service Bulletins, all 
Revision A, and all dated December 8, 2009, which specify a one-time 
inspection of the T/R blades for corrosion or pitting, and repairing or 
replacing the T/R blade if corrosion, pitting, or other damage is 
discovered:
     Alert Service Bulletin (ASB) No. 205-09-102, for Model 
205A and 205A-1 helicopters;
     ASB No. 205B-09-54, for Model 205B helicopters;
     ASB No. 212-09-134, for Model 212 helicopters;
     ASB No. 412-09-136, for Model 412 and 412EP helicopters; 
and
     ASB No. 412CF-09-38, for Model 412CF helicopters.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Proposed AD Requirements

    This proposed AD would continue to require inspecting the T/R 
blades for corrosion and pitting in the forward spar area by following 
specified portions of Bell's service information. In addition to those 
serial-numbered blades that are exempt from the applicability, this 
proposed AD would exclude blades with a S/N prefix of ``BH.''

Costs of Compliance

    We estimate that this proposed AD would affect 384 helicopters of 
U.S. Registry and that labor costs average $85 per work hour. Based on 
these estimates, we expect the following costs:
     Inspecting a T/R blade would require about 10 work-hours 
and no parts for a cost of $850 per helicopter and $326,400 for the 
U.S. fleet.
     Repairing a T/R blade would require 10 work-hours and 
parts would cost $750 for a cost of $1,600 per helicopter.
     Replacing a T/R blade would require about 10 work-hours 
and $28,120 for parts for a cost of $28,970 per blade.

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, 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 removing Airworthiness Directive (AD) 
2011-12-08, Amendment 39-16715 (76 FR 35334, June 17, 2011), and adding 
the following new AD:

Bell Helicopter Textron Inc. (Bell): Docket No. FAA-2018-0866; 
Product Identifier 2018-SW-083-AD.

(a) Applicability

    This AD applies to Bell Model 205A, 205A-1, 205B, 212, 412, 
412CF, and 412EP helicopters, certificated in any category, with a 
tail rotor (T/R) blade part number 212-010-750 (all dash numbers) 
installed, all serial numbers (S/Ns) except:
    (i) S/Ns with a prefix of ``BH''; or
    (ii) S/Ns with a prefix of ``A'' and a number 17061 or larger.

(b) Unsafe Condition

    This AD defines the unsafe condition as a pit or corrosion in 
the forward spar of a T/R blade. This condition could result in a 
crack in the T/R blade, loss of the T/R blade, and subsequent loss 
of control of the helicopter.

(c) Affected ADs

    This AD replaces AD 2011-12-08, Amendment 39-16715 (76 FR 35334, 
June 17, 2011) (AD 2011-12-08).

(d) Comments Due Date

    We must receive comments by June 10, 2019.

(e) 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.

(f) Required Actions

    (1) Within 25 hours time-in-service or 30 days, whichever occurs 
first:
    (i) Remove the T/R hub and blade assembly from the helicopter 
and remove the T/R blade from the hub. Remove the paint from the 
spar area on both sides of the T/R blade by following the 
Accomplishment Instructions, paragraphs 3. through 5., of the 
following Bell Alert Service Bulletins, all Revision A, and all 
dated December 8, 2009: Alert Service Bulletin (ASB) No. 205-09-102 
for the Model 205A and 205A-1 helicopters; ASB No. 205B-09-54 for 
the Model 205B helicopters; ASB No. 212-09-134 for the Model 212 
helicopters; ASB No. 412CF-09-38 for the Model 412CF helicopters; 
and ASB No. 412-09-136 for the Model 412 and 412EP helicopters.
    (ii) Using a 3-power or higher magnifying glass, visually 
inspect both sides of the T/R blade for any corrosion or pitting in 
the spar inspection areas as depicted in Figure 1 of the ASB for 
your model helicopter.

[[Page 14628]]

    (2) Before further flight:
    (i) If you find any corrosion or pitting that is 0.003 inch deep 
or less, either replace the T/R blade with an airworthy T/R blade or 
repair the T/R blade.
    (ii) If you find any corrosion or pitting that is greater than 
0.003 inch deep, replace the T/R blade with an airworthy T/R blade.
    (iii) If any parent material is removed during the sanding 
operation required by paragraph (f)(1)(i) of this AD, either replace 
the T/R blade with an airworthy T/R blade, or repair the T/R blade 
if the parent material removed is within the maximum repair damage 
limits.
    (iv) If there is no corrosion or pitting and no damage greater 
than 0.003 inch deep, refinish the inspection areas and reinstall 
each T/R blade onto the T/R hub, install the T/R assembly on the 
helicopter and track and balance the T/R in accordance with the 
Accomplishment Instructions, paragraphs 8. through 10., of the ASB 
for your model helicopter.

(g) Credit for Previous Actions

    Actions accomplished before the effective date of this AD in 
accordance with the procedures specified in AD 2011-12-08 are 
acceptable for compliance with the corresponding actions specified 
in paragraph (f) of this AD.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, DSCO, FAA, may approve AMOCs for this AD. Send 
your proposal to: Daniel Moore, Aviation Safety Engineer, DSCO 
Branch, Compliance & Airworthiness Division, FAA, 10101 Hillwood 
Pkwy., Fort Worth, TX 76177; telephone 817-222-5418; 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.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6410, Tail Rotor 
Blades.

    Issued in Fort Worth, Texas, on March 29, 2019.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2019-07176 Filed 4-10-19; 8:45 am]
 BILLING CODE 4910-13-P