Document ID: FAA-2016-5422-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Weatherly Aircraft Company Airplanes
Posted Date: 2016-03-31T04:00Z

[Federal Register Volume 81, Number 62 (Thursday, March 31, 2016)]
[Rules and Regulations]
[Pages 18461-18464]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-07228]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5422; Directorate Identifier 2016-CE-011-AD; 
Amendment 39-18456; AD 2016-07-11]
RIN 2120-AA64

Airworthiness Directives; Weatherly Aircraft Company Airplanes

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 all 
Weatherly Aircraft Company Models 201, 201A, 201B, 201C, 620, 620A, 
620B, 620B-TG, and 620TP airplanes. This AD requires visually 
inspecting the center and outer wing front spar lower hinge fittings 
for cracks and corrosion

[[Page 18462]]

and taking all necessary corrective actions. This AD also requires 
sending the inspection results to the FAA. This AD was prompted by a 
report of cracks found on the center wing front spar lower hinge 
fitting. We are issuing this AD to correct the unsafe condition on 
these products.

DATES: This AD is effective April 15, 2016.
    We must receive comments on this AD by May 16, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, 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-2016-
5422; 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 regulatory evaluation, any comments received, and 
other information. The street address for the Docket Office (phone: 
800-647-5527) is in the ADDRESSES section. Comments will be available 
in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Mike Lee, Aerospace Engineer, Los 
Angeles Aircraft Certification Office, FAA, 3960 Paramount Blvd., Suite 
100, Lakewood, California, 90712; phone: (562) 627-5325; fax: (562) 
627-5210; email: mike.s.lee@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    Recently, a Weatherly Aircraft Company Model 620B airplane crashed 
while conducting agricultural operations. Preliminary investigation 
indicates presence of fatigue cracks in the center wing front spar 
lower hinge fitting of the accident aircraft. As a result of voluntary 
operator inspections, an additional cracked fitting in the center wing 
joint was recently reported.
    Investigation reveals that the cracks resulted from fatigue damage 
on the hinge fitting and that routine maintenance practices are not 
finding this damage. This condition, if not detected and corrected, 
could result in failure of the wing front spar lower hinge fittings, 
which could cause the wing to separate and cause loss of control. We 
are issuing this AD to correct the unsafe condition on these products.

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 the same type design.

AD Requirements

    This AD requires visually inspecting the center and outer wing 
front spar lower hinge fittings for cracks and corrosion and taking all 
necessary corrective actions. This AD also requires sending the 
inspection results to the FAA.
    Based on the reports received from the AD requirements, we will 
work with the type certificate holder to evaluate that information to 
determine whether repetitive inspections are necessary and/or a 
possible terminating action. Based on this evaluation, we may initiate 
further rulemaking action to address the unsafe condition identified in 
this AD.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
failure of the wing front spar lower hinge fitting could cause the wing 
to separate from the airplane and cause loss of control. Therefore, we 
find that notice and opportunity for prior public comment are 
impracticable and that good cause exists for making this amendment 
effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite you to send any written data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include the docket number FAA-2016-5422 and 
Directorate Identifier 2016-CE-011-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this AD. We will 
consider all comments received by the closing date and may amend this 
AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 95 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Visually inspect the center and       2 work-hours x $85 per              N/A             $170          $16,150
 outer wing front spar lower hinge     hour = $170.
 fitting.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repair or 
replacement that will be required based on the results of the 
inspection. We have no way of determining the number of aircraft that 
might need this corrective action:

[[Page 18463]]

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
              Action                    Labor cost                Parts cost               Cost per product
----------------------------------------------------------------------------------------------------------------
Replace wing front spar lower      6 work-hours x $85    $800 per fitting...........  $1,310 per fitting.
 hinge fitting.                     per hour = $510 per
                                    fitting.
Remove corrosion on wing front     2 work-hours x $85    N/A........................  $170.
 spar lower hinge fitting.          per hour = $170.
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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 associated with 
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.

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

    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, 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 adding the following new airworthiness 
directive (AD):

2016-07-11 Weatherly Aircraft Company: Amendment 39-18456; Docket 
No. FAA-2016-5422; Directorate Identifier 2016-CE-011-AD.

(a) Effective Date

    This AD is effective April 15, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Weatherly Aircraft Company Models 201, 201A, 
201B, 201C, 620, 620A, 620B, 620B-TG, and 620TP airplanes, all 
serial numbers, that:
    (1) have center and outer wing front spar lower hinge fittings, 
part number 40223 (any dash number configuration), installed; and
    (2) are certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 57, Wing Attach Fittings.

(e) Unsafe Condition

    This AD was prompted by a report of cracks found on the center 
wing front spar lower hinge fitting. We are issuing this AD to 
detect and correct cracks and corrosion in the center and outer wing 
front spar lower hinge fitting, which could cause the fittings to 
fail. Failure of the wing front spar lower hinge fitting could 
result in the wing separating from the airplane and loss of control.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Inspection

    Within the next 30 days after April 15, 2016 (the effective date 
of this AD), do a close visual inspection of the center and outer 
wing front spar lower hinge fittings for cracks and corrosion. Prior 
to the inspection do the following:
    (1) Remove the left and right center wing to outer wing joint 
covers from the airplane.
    (2) Remove the lower forward wing hinge pin bolt caps.

(h) Replacement

    If any cracks are found during the inspection required in 
paragraph (g) of this AD, before further flight, replace the cracked 
wing front spar lower hinge fitting with an airworthy part.

(i) Repair

    If any corrosion is found during the inspection required in 
paragraph (g) of this AD, before further flight, remove up to .020 
inches of the wing front spar lower hinge fitting material in any 
direction to repair corrosion. Replace any parts requiring removal 
of more than .020-inch of wing front spar lower hinge fitting. Any 
operator may request an alternative to the replacement requirement 
using the procedures found in 14 CFR 39.19 and paragraph (m) of this 
AD.

(j) Reporting Requirement

    Within the next 10 days after the inspection required in 
paragraph (g) of this AD or within 10 days after April 15, 2016 (the 
effective date of this AD), whichever occurs later, report the 
result of the inspection to the FAA, Los Angeles Aircraft 
Certification Office (ACO), Attn: Mike Lee, Aerospace Engineer, 3960 
Paramount Blvd. Suite 100, Lakewood, California, 90712; fax: (562) 
627-5210; email: mike.s.lee@faa.gov. Include the following 
information. Please

[[Page 18464]]

identify AD 2016-07-11 in the subject line if submitted through 
email.
    (1) Airplane serial number.
    (2) Hours time-in-service at time of inspection.
    (3) A description of any cracks found.
    (4) A description of any corrosion found.

(k) Special Flight Permit

    Special flight permits are allowed for this AD per 14 CFR 39.23 
for the requirement to remove up to .020 inches of corrosion as 
required in paragraph (i) of this AD. Special flight permits are 
prohibited for all other requirements of this AD.

(l) 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 5 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.

(m) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles ACO, FAA, has the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request 
to your principal inspector or local Flight Standards District 
Office, as appropriate. If sending information directly to the 
manager of the ACO, send it to the attention of the person 
identified in paragraph (n) of this AD.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(n) Related Information

    For information on the subject matter of this AD, contact 
either:
    (1) Weatherly Aircraft Company at phone: (316) 361-0101; email: 
weatherlyaircraft@cox.net; or
    (2) Mike Lee, Aerospace Engineer, Aerospace Engineer, Los 
Angeles Aircraft Certification Office, FAA, 3960 Paramount Blvd. 
Suite 100, Lakewood, California, 90712; phone: (562) 627-5325; fax: 
(562) 627-5210; email: mike.s.lee@faa.gov.

    Issued in Kansas City, Missouri, on March 25, 2016.
Pat Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-07228 Filed 3-30-16; 8:45 am]
 BILLING CODE 4910-13-P