```

[Federal Register Volume 81, Number 207 (Wednesday, October 26, 2016)]
[Rules and Regulations]
[Pages 74285-74287]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-25742]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3821; Directorate Identifier 2014-SW-025-AD; 
Amendment 39-18696; AD 2016-22-07]
RIN 2120-AA64

Airworthiness Directives; Bell Helicopter Textron

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 75-26-05 for 
Bell Helicopter Textron (Bell) Model 204B, 205A-1 and 212 helicopters. 
AD 75-26-05 required 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 new AD requires more frequent 
inspections of certain M/R blades and applies to Model 205A 
helicopters. This AD does not require that helicopter blades be removed 
to conduct the initial visual inspections. We are issuing this AD to 
detect a crack and prevent failure of an M/R blade and subsequent loss 
of helicopter control.

DATES: This AD is effective November 30, 2016.

ADDRESSES: 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 view this referenced service 
information at the FAA, Office of the Regional Counsel, Southwest 
Region, 10101 Hillwood Pkwy, Room 6N-321, Fort Worth, TX 76177.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov in Docket No. FAA-2015-3821; or in person at the 
Docket Management Facility 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 
address for the Docket Office (phone: 800-647-5527) is Document 
Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.

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 
charles.c.harrison@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to remove AD 75-26-05, Amendment 39-2457 (40 FR 57783, December 
12, 1975) and add a new AD. AD 75-26-05 applied to Bell Model 204B, 
205A-1, and 212 helicopters. AD 75-26-05 required removing and visually 
inspecting each M/R blade and, depending on the inspection's outcome, 
repairing or replacing the M/R blade.
    The NPRM published in the Federal Register on May 5, 2016 (81 FR 
27055). The NPRM was prompted by a report of an M/R blade with multiple 
fatigue cracks around the retention bolt hole. The NPRM proposed to 
require more frequent inspections of certain M/R blades and proposed to 
remove the requirement that helicopter blades be removed to conduct the 
initial visual inspections. The NPRM also proposed to include the Model 
205A in the applicability but remove the Model 212 because similar 
inspections are required by AD 2011-23-02 (76 FR 68301, November 4, 
2011). Finally, the NPRM included 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we received no comments on the NPRM (81 FR 27055, May 5, 
2016).

FAA's Determination

    We have reviewed the relevant information and determined that an 
unsafe condition exists and is likely to exist or develop on other 
helicopters of these same type designs and that air safety and the 
public interest require adopting the AD requirements as proposed.

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 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.

Differences Between This AD and the Service Information

    This AD requires 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 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. This AD also applies 
to P/N 204-011-200 because this blade is of the same type and 
susceptible to the unsafe condition. This AD also applies

[[Page 74286]]

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 AD affects 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) requires a half work-hour. No parts are needed. At an 
estimated 24 inspections a year, the cost is $1,032 per helicopter and 
$53,664 for the U.S. fleet.
    Replacing an M/R blade requires 12 work hours and parts 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 have 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 above, 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 a regulatory distinction is required 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.

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 removing Airworthiness Directive (AD) 
75-26-05, Amendment 39-2457 (40 FR 57783, December 12, 1975), and 
adding the following new AD:

2016-22-07 Bell Helicopter Textron: Amendment 39-18696; 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) Effective Date

    This AD becomes effective November 30, 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:
    (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.

[[Page 74287]]

    (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 Permits

    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 7-AVS-ASW-170@faa.gov.
    (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 October 18, 2016.
James A. Grigg,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 2016-25742 Filed 10-25-16; 8:45 am]
 BILLING CODE 4910-13-P
```