[Federal Register Volume 83, Number 11 (Wednesday, January 17, 2018)]
[Rules and Regulations]
[Pages 2358-2360]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-00660]



[[Page 2358]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0895; Product Identifier 2017-SW-048-AD; Amendment 
39-19161; AD 2018-02-08]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for Bell 
Helicopter Textron (Bell) Model 204B, 205A, and 205A-1 helicopters with 
a Helicopter Technology Company (HTC) main rotor (M/R) blade installed. 
This AD requires cleaning and visually inspecting the M/R blades, and 
depending on the outcome of the inspection, repairing or replacing the 
M/R blades. This AD is prompted by a report of an M/R blade with a 
fatigue crack in the grip plate and doublers at the blade retention 
bolt hole. The actions of this AD are intended to correct an unsafe 
condition on these products.

DATES: This AD becomes effective February 1, 2018.
    We must receive comments on this AD by March 19, 2018.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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-2017-
0895; 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 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 final 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 the referenced 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: Galib Abumeri, Aerospace Engineer 
(Structures), Airframe Section, Los Angeles ACO Branch, Compliance and 
Airworthiness Division, FAA, 3960 Paramount Blvd., Lakewood, California 
90712; telephone 562-627-5324; email <a href="/cdn-cgi/l/email-protection#7710161b1e15591615021a12051e3711161659101801"><span class="__cf_email__" data-cfemail="355254595c571b5457405850475c755354541b525a43">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments prior to it becoming effective. However, 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 resulted 
from adopting this AD. The most helpful comments reference a specific 
portion of the AD, 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 them 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 rulemaking during the 
comment period. We will consider all the comments we receive and may 
conduct additional rulemaking based on those comments.

Discussion

    We are adopting a new AD for Bell 204B, 205A and 205A-1 helicopters 
with an HTC M/R blade part number (P/N) 204P2100-101 installed. This AD 
requires repetitive inspections of the exposed areas of the lower grip 
pad and upper and lower grip plates of each M/R blade for a crack, 
corrosion, an edge void, loose or damaged adhesive squeeze-out, and an 
edge delamination.
    The actions of this AD are the same as those required by AD 2016-
22-07 (81 FR 74285, October 26, 2016), which applies to Bell Model 
204B, 205A and 205A-1 helicopters with an M/R blade P/N 204-011-200-001 
or P/N 204-011-250-(all dash numbers) installed. AD 2016-22-07 was 
prompted by a report of an M/R blade with multiple fatigue cracks 
around the retention bolt hole.
    This AD is prompted by a report that during a ground inspection, a 
crack was discovered in the grip plate and doublers at the blade 
retention bolt hole of a UH-1B helicopter model. The blade, which HTC 
produced for restricted category and commercial model helicopters, had 
926 hours TIS and is of the same design as the M/R blades in AD 2016-
22-07. We are issuing this AD to detect or prevent a crack, which could 
lead to failure of an M/R blade and subsequent loss of helicopter 
control.

FAA's Determination

    We are issuing 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

    HTC has issued Service Notice No. 204-2100-1 on July 5, 2017, for 
affected helicopters with M/R blade P/N 204P2100-101, serial numbers 
A099 through A119 installed. This service notice specifies cleaning and 
visually inspecting the M/R blades and depending on the outcome, 
repairing or replacing the blades in accordance with AD 2016-23-09.
    We also reviewed Bell Helicopter Alert Service Bulletin (ASB) No. 
UH-1H-13-09, dated January 14, 2013, for the Model UH-1H helicopter. 
ASB No. 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 No. UH-1H-13-09 also specifies a repetitive and more 
detailed visual inspection, daily and at every 150 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.
    Lastly, we reviewed Bell Helicopter ASB No. 204-75-1 for Model 204B 
helicopters and ASB No. 205-75-5 for Model 205A-1 helicopters, both 
Revision C and both dated April 25, 1979. ASB No. 204-75-1 and ASB No. 
205-75-5 specify visually inspecting

[[Page 2359]]

the M/R blades during each daily inspection. ASB No. 204-75-1 and ASB 
No. 205-75-5 also provide instructions for repetitively inspecting the 
blades every 1,000 hours of operation or every 12 months, whichever 
occurs first.

AD Requirements

    This AD requires 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, cleaning 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, this AD also requires 
visually inspecting various M/R blade parts for a crack or corrosion. 
If there is a crack, corrosion, an edge void, loose or damaged adhesive 
squeeze-out, or an edge delamination, before further flight, this AD 
requires repairing the M/R blade or replacing it with an airworthy M/R 
blade, depending on whether the condition is within maximum repair 
damage limits.
    This AD also requires reporting information about any cracks found 
during the inspection to the FAA within 10 days.

Differences Between This AD and the Service Information

    This AD requires all inspections every 25 hours TIS or 2 weeks, 
whichever occurs first. 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. The service 
information applies to Bell M/R blade P/N 204-011-250. This AD applies 
to HTC M/R blade P/N 204P2100-101.

Interim Action

    We consider this AD to be an interim action. The notification of a 
crack in the M/R blade that is required by this AD may enable us to 
obtain better insight into the cause of the M/R blade cracking. This 
information may help us develop additional action to address this 
unsafe condition. Once this action is developed, approved, and 
available, we might consider additional rulemaking.

Costs of Compliance

    We estimate that this AD affects 10 helicopters of U.S. Registry 
and that labor costs average $85 per work-hour. Based on these 
estimates, we expect the following costs:
    <bullet> Cleaning and performing all inspections of a set of M/R 
blades (2 per helicopter) requires 0.5 work-hour for a cost of $43 per 
helicopter and $430 for the U.S. fleet per inspection cycle.
    <bullet> Replacing an M/R blade requires 12 work-hours and parts 
cost $86,000 for a total cost of $87,020 per blade.
    <bullet> Reporting the inspection results required by this AD will 
require about 0.5 work-hour for a cost of $43 per helicopter and $430 
for the U.S. fleet per report.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting required by this AD 
is mandatory. Comments concerning the accuracy of this burden and 
suggestions for reducing the burden should be directed to the FAA at 
800 Independence Ave. SW, Washington, DC 20591. ATTN: Information 
Collection Clearance Officer, AES-200.

FAA's Justification and Determination of the Effective Date

    Providing an opportunity for public comments prior to adopting 
these AD requirements would delay implementing the safety actions 
needed to correct this known unsafe condition. Therefore, we find that 
the risk to the flying public justifies waiving notice and comment 
prior to the adoption of this rule because the required corrective 
actions must be accomplished within two weeks.
    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we determined that notice and opportunity for 
prior public comment before issuing this AD are impracticable and that 
good cause exists to make this AD effective in less than 30 days.

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 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, 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):

2018-02-08 Bell Helicopter Textron: Amendment 39-19161; Docket No.

[[Page 2360]]

FAA-2017-0895; Product Identifier 2017-SW-048-AD.

(a) Applicability

    This AD applies to Bell Helicopter Textron (Bell) Model 204B, 
205A, and 205A-1 helicopters with a Helicopter Technology Company 
(HTC) main rotor (M/R) blade part number 204P2100-101 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) Effective Date

    This AD becomes effective February 1, 2018.

(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

    (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:
    (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 (e)(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 (e)(2)(vi) or (e)(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.
    (3) If there is a crack during any inspection in paragraph 
(e)(1) of this AD, within 10 days after completing the inspection, 
report the information requested in Appendix 1 to this AD by mail to 
the Los Angeles ACO Branch, Compliance and Airworthiness Division, 
FAA, 3960 Paramount Blvd., Lakewood, California 90712; attn. Galib 
Abumeri; or by email to <a href="/cdn-cgi/l/email-protection#e88f8984818ac6898a9d858d9a81a88e8989c68f879e"><span class="__cf_email__" data-cfemail="4a2d2b262328642b283f272f38230a2c2b2b642d253c">[email protected]</span></a>.

 (f) Special Flight Permits

    Special flight permits are prohibited.

 (g) Paperwork Reduction Act Burden Statement

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty 
for failure to comply with a collection of information subject to 
the requirements of the Paperwork Reduction Act unless that 
collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 30 minutes per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles ACO Branch, FAA, may approve AMOCs 
for this AD. Send your proposal to: Galib Abumeri, Aerospace 
Engineer (Structures), Airframe Section, Los Angeles ACO Branch, 
Compliance and Airworthiness Division, FAA, 3960 Paramount Blvd., 
Lakewood, California 90712; telephone 562-627-5324; email 
<a href="/cdn-cgi/l/email-protection#640305080d064a0506110901160d240205054a030b12"><span class="__cf_email__" data-cfemail="9bfcfaf7f2f9b5faf9eef6fee9f2dbfdfafab5fcf4ed">[email protected]</span></a>.
    (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

    HTC Service Notice No. 204-2100-1, dated July 5, 2017; Alert 
Service Bulletin (ASB) No. UH-1H-13-09, dated January 14, 2013; Bell 
ASB No. 204-75-1 and Bell 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 this 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 January 9, 2018.
James A. Grigg,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.

Appendix 1 to AD 2018-02-08

    Please report the following information by mail to the Los 
Angeles ACO Branch, Compliance and Airworthiness Division, FAA, 3960 
Paramount Blvd., Lakewood, California 90712; attn. Galib Abumeri; or 
by email to <a href="/cdn-cgi/l/email-protection#3b5c5a575259155a594e565e49527b5d5a5a155c544d"><span class="__cf_email__" data-cfemail="accbcdc0c5ce82cdced9c1c9dec5eccacdcd82cbc3da">[email protected]</span></a>.
    (1) Date of inspection:
    (2) Aircraft N-number:
    (3) M/R blade serial number:
    (4) M/R blade hours of time-in-service:
    (5) Location of each crack:
    (6) Dimension of each crack:
    (7) Primary operating location of the M/R blade:

[FR Doc. 2018-00660 Filed 1-16-18; 8:45 am]
 BILLING CODE 4910-13-P


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