[Federal Register Volume 81, Number 87 (Thursday, May 5, 2016)]
[Proposed Rules]
[Pages 27055-27057]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-10523]



[[Page 27055]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3821; Directorate Identifier 2014-SW-025-AD
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede airworthiness directive (AD) 75-26-05 
for Bell Helicopter Textron (Bell) Model 204B, 205A-1 and 212 
helicopters. AD 75-26-05 currently requires removing and visually 
inspecting each main rotor (M/R) blade and, depending on the 
inspection's outcome, repairing or replacing the M/R blades. This 
proposed AD would require more frequent inspections of certain M/R 
blades and would also apply to Model 205A helicopters. This proposed AD 
would have no requirement that helicopter blades be removed to conduct 
the initial visual inspections. These proposed actions are intended to 
detect a crack and prevent failure of an M/R blade and subsequent loss 
of helicopter control.

DATES: We must receive comments on this proposed AD by July 5, 2016.

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-2015-
3821; 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.
    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: Charles Harrison, Project Manager, 
Fort Worth Aircraft Certification Office, FAA, 10101 Hillwood Pkwy., 
Fort Worth, TX 76177; telephone (817) 222-5140; 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

    On December 3, 1975, we issued AD 75-26-05, Amendment 39-2457 (40 
FR 57783, December 12, 1975) for Bell Model 204B, 205A-1, and 212 
helicopters. AD 75-26-05 requires, at intervals not to exceed 12 months 
installed time, visually inspecting the grip pad, grip plates, 
doublers, drag plates, and adjacent surfaces for voids, edge voids, 
corrosion, cracks, and adhesive squeeze-out along bond lines. AD 75-26-
05 prohibits returning to service any blade with a crack or an adhesive 
void exceeding certain limits. For damage within certain limits, the M/
R blade can be repaired, refinished, and reinstalled.
    AD 75-26-05 was prompted by an evaluation of a cracked M/R blade 
that concludes that initial cracking resulted from corrosion. These 
actions were intended to detect a crack and corrosion and prevent 
further corrosion in the M/R blade inboard portion.

Actions Since AD 75-26-05 Was Issued

    Since we issued AD 75-26-05, Bell has evaluated an M/R blade 
installed on a Model UH-1H helicopter with multiple fatigue cracks 
around the blade retention bolt hole. The cracks resulted from a void 
between the lower grip plate and the grip pad. A ``substantial'' void 
also was found at the outboard doubler tip on the lower blade surface. 
Different part-numbered M/R blades of the same type may also be 
installed on Model 204B, 205A, and 205A-1 helicopters. We have 
determined that more frequent inspections than those required by AD 75-
26-05 are necessary to detect cracking or certain damage. While AD 75-
26-05 requires removing the blades from the M/R hub, the inspections in 
this proposed AD would not. AD 75-26-05 applies to the Model 212 
helicopter, and this proposed AD would not because similar inspections 
on Model 212 blades addressing the unsafe condition are required by AD 
2011-23-02 (76 FR 68301, November 4, 2011). We are including specific 
part-numbered blades in the applicability so that the proposed AD would 
no longer be required if a new blade is designed that is not subject to 
the unsafe condition.

FAA's Determination

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

Related Service Information

    Bell issued Alert Service Bulletin (ASB) No. UH-1H-13-09, dated 
January 14, 2013, for the Model UH-1H helicopter (ASB UH-1H-13-09). ASB 
UH-1H-13-09 specifies a one-time visual inspection, within 10 hours 
time-in-service (TIS), of the lower grip pad and upper and lower grip 
plates for cracks, edge voids, and loose or damaged adhesive squeeze-
out. ASB UH-1H-13-09 also specifies a repetitive visual inspection, 
daily and at every 150

[[Page 27056]]

hours TIS, of the lower grip pad, upper and lower grip plates, and all 
upper and the lower doublers for cracks, corrosion, edge voids, and 
loose or damaged adhesive squeeze-out. Similar inspections are 
contained in Bell ASB No. 204-75-1 (ASB 204-75-1) and No. 205-75-5 (ASB 
205-75-5), both Revision C and both dated April 25, 1979, for Bell 
Model 204B and 205A-1 helicopters, respectively. ASB 204-75-1 and ASB 
205-75-5 call for daily inspections and for inspections, rework, and 
refinishing every 1,000 hours TIS or 12 months, whichever occurs first.

Proposed AD Requirements

    This proposed AD would require within 25 hours TIS or 2 weeks, 
whichever occurs first, and thereafter at intervals not to exceed 25 
hours TIS or 2 weeks, whichever occurs first, cleaning the upper and 
lower surfaces of each M/R blade from an area starting at the butt end 
of the blade to three inches outboard of the doublers. The proposed AD 
also would require visually inspecting various M/R parts for a crack or 
corrosion using a 3X or higher power magnifying glass and a light.
    If there is a crack, corrosion, an edge void, loose or damaged 
adhesive squeeze-out, or an edge delamination before further flight, 
this proposed AD would require repairing the M/R blade or replacing it 
with an airworthy M/R blade, depending on the condition's severity.

Differences Between This Proposed AD and the Service Information

    The proposed AD would require all inspections every 25 hours TIS or 
2 weeks, whichever occurs first. ASB UH-1H-13-09 specifies a one-time 
inspection within 10 hours TIS, and then a second repetitive inspection 
daily and at every 150 hours TIS, while ASB 204-75-1 and ASB 205-75-5 
call for daily visual inspections, and inspections, rework, and 
refinishing every 1,000 hours TIS or 12 months, whichever occurs first. 
This proposed AD contains more detailed inspection requirements and a 
more specific inspection area than the instructions in ASB UH-1H-13-09. 
The service information applies to M/R blade, part number (P/N) 204-
011-250, and was issued for Model 204B and 205A-1 helicopters. The 
proposed AD also applies to P/N 204-011-200, because this blade is of 
the same type and susceptible to the unsafe condition. The proposed AD 
also applies to certain M/R blades installed on the Model 205A 
helicopters. While none of these models are registered in the U.S., 
they were included because of blade P/N eligibility.

Costs of Compliance

    We estimate that this proposed AD would affect 52 helicopters of 
U.S. Registry and that labor costs average $85 a work-hour. Based on 
these estimates, we expect the following costs:
    Cleaning and performing all inspections of a set of M/R blades (2 
per helicopter) would require a half work-hour. No parts would be 
needed. At an estimated 24 inspections a year, the cost would be $1,032 
per helicopter and $53,664 for the U.S. fleet.
    Replacing an M/R blade would require 12 work hours and parts would 
cost $90,656 for a total cost of $91,676 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) 
No. 75-26-05, Amendment 39-2457 (40 FR 57783, December 12, 1975), and 
adding the following new AD:

Bell Helicopter Textron: Docket No. FAA-2015-3821; Directorate 
Identifier 2014-SW-025-AD.

(a) Applicability

    This AD applies to Model 204B, 205A, and 205A-1 helicopters with 
a main rotor (M/R) blade, part number (P/N) 204-011-200-001 or P/N 
204-011-250-(all dash numbers), installed, certificated in any 
category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in an M/R blade, 
which could result in failure of an M/R blade and subsequent loss of 
helicopter control.

(c) Affected ADs

    This AD supersedes AD 75-26-05, Amendment 39-2457 (40 FR 57783, 
December 12, 1975).

(d) Comments Due Date

    We must receive comments by July 5, 2016.

(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 (TIS) or 2 weeks, whichever 
occurs first, and thereafter at intervals not to exceed 25 hours TIS 
or 2 weeks, whichever occurs first, clean the upper and lower 
exposed surfaces of each M/R blade from an area starting at the butt 
end of the blade to three inches outboard of the doublers. Using a 
3X or higher power magnifying glass and a light, inspect as follows:

[[Page 27057]]

    (i) Visually inspect the exposed areas of the lower grip pad and 
upper and lower grip plates of each M/R blade for a crack and any 
corrosion.
    (ii) On the upper and lower exposed surfaces of each M/R blade 
from blade stations 24.5 to 35 for the chord width, visually inspect 
each layered doubler and blade skin for a crack and any corrosion. 
Pay particular attention for any cracking in a doubler or skin near 
or at the same blade station as the blade retention bolt hole (blade 
station 28).
    (iii) Visually inspect the exposed areas of each bond line at 
the edges of the lower grip pad, upper and lower grip plates, and 
each layered doubler (bond lines) on the upper and lower surfaces of 
each M/R blade for the entire length and chord width for an edge 
void, any corrosion, loose or damaged adhesive squeeze-out, and an 
edge delamination. Pay particular attention to any crack in the 
paint finish that follows the outline of a grip pad, grip plate, or 
doubler, and to any loose or damaged adhesive squeeze-out, as these 
may be the indication of an edge void.
    (2) If there is a crack, any corrosion, an edge void, loose or 
damaged adhesive squeeze-out, or an edge delamination during any 
inspection in paragraph (f)(1) of this AD, before further flight, do 
the following:
    (i) If there is a crack in a grip pad or any grip plate or 
doubler, replace the M/R blade with an airworthy M/R blade.
    (ii) If there is a crack in the M/R blade skin that is within 
maximum repair damage limits, repair the M/R blade. If the crack 
exceeds maximum repair damage limits, replace the M/R blade with an 
airworthy M/R blade.
    (iii) If there is any corrosion within maximum repair damage 
limits, repair the M/R blade. If the corrosion exceeds maximum 
repair damage limits, replace the M/R blade with an airworthy M/R 
blade.
    (iv) If there is an edge void in the grip pad or in a grip plate 
or doubler, determine the length and depth using a feeler gauge. 
Repair the M/R blade if the edge void is within maximum repair 
damage limits, or replace the M/R blade with an airworthy M/R blade.
    (v) If there is an edge void in a grip plate or doubler near the 
outboard tip, tap inspect the affected area to determine the size 
and shape of the void. Repair the M/R blade if the edge void is 
within maximum repair damage limits, or replace the M/R blade with 
an airworthy M/R blade.
    (vi) If there is any loose or damaged adhesive squeeze-out along 
any of the bond lines, trim or scrape away the adhesive without 
damaging the adjacent surfaces or parent material of the M/R blade. 
Determine if there is an edge void or any corrosion by lightly 
sanding the trimmed area smooth using 280 or finer grit paper. If 
there is no edge void or corrosion, refinish the sanded area.
    (vii) If there is an edge delamination along any of the bond 
lines or a crack in the paint finish, determine if there is an edge 
void or a crack in the grip pad, grip plate, doubler, or skin by 
removing paint from the affected area by lightly sanding in a span-
wise direction using 180-220 grit paper. If there are no edge voids 
and no cracks, refinish the sanded area.
    (viii) If any parent material is removed during any sanding or 
trimming in paragraphs (f)(2)(vi) or (f)(2)(vii) of this AD, repair 
the M/R blade if the damage is within maximum repair damage limits, 
or replace the M/R blade with an airworthy M/R blade.

(g) Special Flight Permit

    Special flight permits are prohibited.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Fort Worth Aircraft Certification Office, FAA, 
may approve AMOCs for this AD. Send your proposal to: Charles 
Harrison, Project Manager, Fort Worth Aircraft Certification Office, 
FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222-
5140; 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) Additional Information

    Bell Helicopter Alert Service Bulletin (ASB) No. UH-1H-13-09, 
dated January 14, 2013, and ASB No. 204-75-1 and ASB No. 205-75-5, 
both Revision C and both dated April 25, 1979, which are not 
incorporated by reference, contain additional information about the 
subject of this AD. For service information identified in this AD, 
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 the service information 
at the FAA, Office of the Regional Counsel, Southwest Region, 10101 
Hillwood Pkwy, Room 6N-321, Fort Worth, TX 76177.

(j) Subject

    Joint Aircraft Service Component (JASC) Code: 6210, Main Rotor 
Blades.

    Issued in Fort Worth, Texas, on April 15, 2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-10523 Filed 5-4-16; 8:45 am]
 BILLING CODE 4910-13-P