81 FR 21288 - Airworthiness Directives; Various Restricted Category Helicopters

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 69 (April 11, 2016)

We propose to adopt a new airworthiness directive (AD) for various restricted category helicopters. This proposed AD would require cleaning and visually inspecting certain main rotor (M/R) blades and, depending on the outcome of the inspections, repairing or replacing the M/R blades. This proposed AD is prompted by a report of an M/R blade with multiple fatigue cracks around the blade retention bolt hole. The proposed actions are intended to detect a crack in the M/R blade, and prevent failure of the M/R blade and subsequent loss of helicopter control.

[Federal Register Volume 81, Number 69 (Monday, April 11, 2016)]
[Proposed Rules]
[Pages 21288-21290]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-07985]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3820; Directorate Identifier 2014-SW-024-AD]
RIN 2120-AA64


Airworthiness Directives; Various Restricted Category 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 
various restricted category helicopters. This proposed AD would require 
cleaning and visually inspecting certain main rotor (M/R) blades and, 
depending on the outcome of the inspections, repairing or replacing the 
M/R blades. This proposed AD is prompted by a report of an M/R blade 
with multiple fatigue cracks around the blade retention bolt hole. The 
proposed actions are intended to detect a crack in the M/R blade, and 
prevent failure of the M/R blade and subsequent loss of helicopter 
control.

DATES: We must receive comments on this proposed AD by June 10, 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-
3820 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 the referenced service 
information at the FAA, Office of the Regional Counsel, Southwest 
Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, Texas 76177.

FOR FURTHER INFORMATION CONTACT: Charles Harrison, Project Manager, 
Fort Worth Aircraft Certification Office, 10101 Hillwood Pkwy., Fort 
Worth, Texas 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.

[[Page 21289]]

Discussion

    We propose to adopt a new AD for Model TH-1F, UH-1B, UH-1F, UH-1H, 
and UH-1P restricted category helicopters. This proposed AD would 
require repetitively cleaning and visually inspecting the M/R blades 
for a crack, corrosion, an edge void, loose or damaged adhesion, and an 
edge delamination. Depending on the results of the inspections, this 
proposed AD would require either repairing or replacing the M/R blades.
    This proposed AD is prompted by a Bell Helicopter Textron Inc. 
(BHTI) evaluation of an M/R blade installed on a Model UH-1H helicopter 
that had 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. A different part-numbered M/R blade of 
the same type installed on the Model UH-1H helicopter may also be 
installed on Model TH-1F, UH-1B, UH-1F, and UH-1P helicopters. The 
proposed actions are intended to detect a crack in an M/R blade, and 
prevent failure of the M/R blade, and subsequent loss of helicopter 
control.

FAA's Determination

    We are proposing this AD because we evaluated all known relevant 
information and determined that an unsafe condition exists and is 
likely to exist or develop on other products of these same type 
designs.

Related Service Information

    Bell Helicopter issued 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.
    Bell Helicopter Textron also issued 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 call for visually inspecting the M/R blades during each daily 
inspection and repetitively washing the blades and applying WD-40. 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, or within 150 hours or 30 
days, whichever occurs first, if the blades have more than 1,000 hours 
of operation or have been in service more than 12 months. While ASB No. 
204-75-1 and ASB No. 205-75-5 do not apply to the helicopters that are 
the subject of this proposed AD, they do apply to the affected M/R 
blades.

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

    ASB No. UH-1H-13-09 specifies a one-time inspection and then a 
second repetitive inspection daily and at every 150 hours TIS, and ASB 
No. 204-75-1 and ASB 205-75-5 call for visually inspecting the M/R 
blades daily and every 1,000 hours TIS or 12 months, whichever occurs 
first. The proposed AD would require all inspections at intervals not 
to exceed 25 hours TIS or two weeks, whichever occurs first. This 
proposed AD contains more detailed inspection requirements and a more 
specific inspection area than the instructions in ASB No. UH-1H-13-09. 
Lastly, ASB No. UH-1H-13-09 applies to Model UH-1H helicopters with M/R 
blade P/N 204-011-250-113, ASB No. 204-75-1 applies to Model 204B 
helicopters with M/R blade P/N 204-011-0250 (all dash numbers), and ASB 
No. 205-75-5 applies to Model 205A-1 helicopters with M/R blade P/N 
204-011-0250 (all dash numbers). This proposed AD would apply to Model 
TH-1F, UH-1B, UH-1F, UH-1H, and UH-1P helicopters with M/R blade P/N 
204-011-250-005 or 204-011-250-113.

Costs of Compliance

    We estimate that this proposed AD would affect 607 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 total of \1/2\ work-hour. No 
parts would be needed. At an estimated 24 inspections a year, the cost 
would be $1,032 per helicopter and $626,424 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.

[[Page 21290]]

    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):

Various Restricted Category Helicopters: Docket No. FAA-2015-3820; 
Directorate Identifier 2014-SW-024-AD.

(a) Applicability

    This AD applies to Model TH-1F, UH-1B, UH-1F, UH-1H, and UH-1P 
helicopters with a main rotor (M/R) blade, part number 204-011-250-
005 or 204-011-250-113, installed.

(b) Unsafe Condition

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

(c) Comments Due Date

    We must receive comments by June 10, 2016.

(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 area 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 entire 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.

(f) Special Flight Permit

    Special flight permits are prohibited.

(g) Alternative Methods of Compliance (AMOC)

    (1) The Manager, Rotorcraft Certification Office, FAA, may 
approve AMOCs for this AD. Send your proposal to: Charles Harrison, 
Project Manager, Fort Worth Aircraft Certification Office, 10101 
Hillwood Pkwy., Fort Worth, Texas 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.

(h) Additional Information

    Bell Helicopter Alert Service Bulletin (ASB) No. UH-1H-13-09, 
dated January 14, 2013, and Bell Helicopter Textron ASB No. 204-75-1 
and ASB 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 a 
copy of information at the FAA, Office of the Regional Counsel, 
Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, 
Texas 76177.

(i) Subject

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

    Issued in Fort Worth, Texas, on March 29, 2016.
James A. Grigg,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-07985 Filed 4-8-16; 8:45 am]
 BILLING CODE 4910-13-P