[Federal Register Volume 82, Number 196 (Thursday, October 12, 2017)]
[Rules and Regulations]
[Pages 47371-47373]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-21443]



[[Page 47371]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0648; Product Identifier 2017-CE-012-AD; Amendment 
39-19070; AD 2017-20-13]
RIN 2120-AA64


Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A. 
Airplanes

AGENCY:  Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for PIAGGIO 
AERO INDUSTRIES S.p.A. Model P-180 airplanes. This AD results from 
mandatory continuing airworthiness information (MCAI) originated by an 
aviation authority of another country to identify and correct an unsafe 
condition on an aviation product. The MCAI describes the unsafe 
condition as disbonding of the upper and lower metal skin from the 
honeycomb core on the elevator assembly and other flight control 
surfaces. We are issuing this AD to require actions to address the 
unsafe condition on these products.

DATES: This AD is effective November 16, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 16, 
2017.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0638; or in person at 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 service information identified in this AD, contact PIAGGIO AERO 
INDUSTRIES S.p.A--Continued Airworthiness, Via Pionieri e Aviatori 
d'Italia snc--16154 Genova, Italy; Telephone: +39 010 0998046; Fax: 
None; email: <a href="/cdn-cgi/l/email-protection#83e2eaf1f4ecf1f7ebeaede6f0f0c3f3eae2e4e4eaece2e6f1ecf0f3e2e0e6adeaf7"><span class="__cf_email__" data-cfemail="61000813160e131509080f041212211108000606080e0004130e12110002044f0815">[email protected]</span></a>; Internet: 
www.piaggioaerospace.it/en/customer-support#care. You may view this 
referenced service information at the FAA, Policy and Innovation 
Division, 901 Locust, Kansas City, Missouri 64106. For information on 
the availability of this material at the FAA, call (816) 329-4148. It 
is also available on the Internet at http://www.regulations.gov by 
searching for Docket No. FAA-2017-0648.

FOR FURTHER INFORMATION CONTACT: Mike Kiesov, Aerospace Engineer, FAA, 
Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4144; fax: (816) 329-4090; email: 
<a href="/cdn-cgi/l/email-protection#462b2f2d23682d2f233529300620272768212930"><span class="__cf_email__" data-cfemail="620f0b09074c090b07110d14220403034c050d14">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain PIAGGIO AERO 
INDUSTRIES S.p.A. Model P-180 airplanes. The NPRM was published in the 
Federal Register on June 29, 2017 (82 FR 29445). The NPRM proposed to 
correct an unsafe condition for the specified products and was based on 
mandatory continuing airworthiness information (MCAI) originated by an 
aviation authority of another country. The MCAI states:

    During a post flight inspection of a right hand (RH) elevator 
assembly, disbonding was detected on the upper and lower metal skin 
from the honeycomb core. Subsequent investigation identified that a 
manufacturing deficiency caused the detected disbonding and that 
other flight control surfaces could potentially be affected by the 
same deficiency.
    This condition, if not detected and corrected, could reduce the 
structural stiffness of the flight control surface and downgrade its 
aerodynamic characteristics, possibly resulting in reduced control 
of the aeroplane.
    To address this potential unsafe condition, Piaggio Aero 
Industries (PAI) issued Service Bulletin (SB) 80-0455 to provide 
inspection instructions.
    For the reasons described above, this [EASA] AD requires 
repetitive inspections of the affected flight control assemblies 
and, depending on findings, repair or replacement. This [EASA] AD 
also requires reporting of the inspection result to PAI.

    The MCAI can be found in the AD docket on the Internet at https://www.regulations.gov/document?D=FAA-2017-064-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed PIAGGIO AERO INDUSTRIES S.p.A. Mandatory Service 
Bulletin N.: 80-0455, dated: January 13, 2017. This service information 
describes procedures for repetitive inspections to verify the 
structural integrity of the flight control assemblies. This service 
information is reasonably available because the interested parties have 
access to it through their normal course of business or by the means 
identified in the ADDRESSES section of this AD.

Costs of Compliance

    We estimate that this AD will affect 103 products of U.S. registry. 
We also estimate that it will take 9 work-hours per product to comply 
with the basic requirements of this AD. The average labor rate is $85 
per work-hour.
    Based on these figures, we estimate the cost of this AD on U.S. 
operators to be $78,795, or $765 per product.
    The scope of damage found in the required inspections could vary 
significantly from airplane to airplane. We have no way of determining 
how much damage may be found on each airplane or the cost to repair 
damaged parts on each airplane.
    In addition, we have no way of knowing how many products may need 
replacement as a result of the required inspections. The following cost 
estimates were obtained directly from the manufacturer and we estimate 
that any necessary follow-on replacement actions would cost as follows:
    (i) Control surface repair: 10 work-hours for a cost of $850 per 
product.
    (ii) Left Hand (LH) Forward Wing Flap Replacement: 4 work-hours and 
require parts costing $30,079, for a total cost of $30,419.
    (iii) Right Hand (RH) Forward Wing Flap Replacement: 4 work-hours 
and require parts costing $30,079, for a total cost of $30,419.
    (iv) LH Aileron Assembly: 7 work-hours and require parts costing 
$40,715, for a total cost of $41,310.
    (v) RH Aileron Assembly: 7 work-hours and require parts costing 
$86,050, for a total cost of $86,645.
    (vi) Main Wing LH Inboard Flap Assembly: 4 work-hours and require 
parts costing $22,699, for a total cost of $23,039.
    (vii) Main Wing RH Inboard Flap Assembly: 4 work-hours and require

[[Page 47372]]

parts costing $22,699, for a total cost of $23,039.
    (viii) LH Elevator Assembly: 8 work-hours and require parts costing 
$59,917, for a total cost of $60,597.
    (ix) RH Elevator Assembly: 8 work-hours and require parts costing 
$59,917, for a total cost of $60,597.
    There is an additional 10 work-hours that may be required for post-
repair or post-installation replacement of flight control surface 
adjustments and testing, for a total cost of $850.

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to small airplanes and domestic 
business jet transport airplanes to the Director of the Policy and 
Innovation Division.

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 above, I certify this AD:
    (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, 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.

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-
0648; 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 the NPRM, the regulatory evaluation, any comments received, 
and other information. The street address for the Docket Office 
(telephone (800) 647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

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 AD:

2017-20-13 Piaggio Aero Industries S.p.A.: Amendment 39-19070; 
Docket No. FAA-2017-0648; Product Identifier 2017-CE-012-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective November 16, 
2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to PIAGGIO AERO INDUSTRIES S.p.A. P-180 
airplanes, serial numbers 1002, 1004 through 1220, that are:
    (1) Equipped with flight control surfaces part numbers (P/Ns) 
and serial numbers (S/Ns) not listed in table 1 of PIAGGIO AERO 
INDUSTRIES S.p.A. Mandatory Service Bulletin N.: 80-0455, dated: 
January 13, 2017 (PAI SB No. 80-0455); and
    (2) certificated in any category.

(d) Subject

    Air Transport Association of America (ATA) Code 27: Flight 
Controls.

(e) Reason

    This AD was prompted by mandatory continuing airworthiness 
information (MCAI) originated by an aviation authority of another 
country to identify and correct an unsafe condition on an aviation 
product. The MCAI describes the unsafe condition as disbonding of 
the upper and lower metal skin from the honeycomb core on the 
elevator assembly and other flight control surfaces. We are issuing 
this AD to prevent structural stiffness of the flight control 
surface and the downgrade of its aerodynamic characteristics, 
resulting in reduced control.

(f) Actions and Compliance

    Unless already done, do the actions in paragraphs (f)(1) through 
(8) of this AD. The parts affected by this AD are all left hand (LH) 
forward flaps, right hand (RH) forward flaps, main wing LH inboard 
flaps, main wing RH inboard flaps, LH ailerons, RH ailerons, LH 
elevators, and RH elevators, hereafter referred to as ``affected 
control surface'' in this AD.
    (1) Within the next 50 hours time-in-service (TIS) after 
November 16, 2017 (the effective date of this AD) or within the next 
200 hours TIS after the last coin tapping inspection of the affected 
control surface following PAI Non-Destructive Test Manual (NDTM) 
180-MAN-0300-01107, Chapter 51-00-01; whichever occurs later, do a 
coin tapping inspection of each affected control surface. 
Repetitively thereafter inspect at the intervals specified in 
paragraphs (f)(3)(i) and (ii). Follow Part B of the Accomplishment 
Instructions in PAI SB No. 80-0455.
    (i) Do two repetitive inspections at intervals not to exceed 200 
hours TIS; and
    (ii) Repetitively thereafter inspect at intervals not to exceed 
600 hours TIS.
    (2) If damage is found during any inspection required in 
paragraph (f)(1) of this AD, before further flight, repair or 
replace as necessary each damaged affected control surface following 
Part B and/or C of the Accomplishment Instructions in PAI SB No. 80-
0455.
    (3) Within 50 hours TIS after the repair of an affected control 
surface as required by paragraph (f)(2) of this AD, do a coin 
tapping inspection of that repaired affected control surface. 
Repetitively thereafter inspect at the intervals specified in 
paragraphs (f)(3)(i) and (ii) of this AD. Follow the instructions in 
PAI SB No. 80-0455.
    (i) Do two repetitive inspections at intervals not to exceed 200 
hours TIS; and
    (ii) Repetitively thereafter inspect at intervals not to exceed 
600 hours TIS.
    (4) If damage is found during any inspection required in 
paragraph (f)(3) of this AD, before further flight, repair or 
replace as necessary each damaged affected control surface following 
the instructions in Part B and/or C of the Accomplishment 
Instructions in PAI SB No. 80-0455.
    (5) Repair of an affected control surface, as required by 
paragraph (f)(2) or (4) of this AD, does not constitute terminating 
action for repetitive inspections as required by this AD

[[Page 47373]]

for that affected control surface, unless the FAA-approved repair 
instructions specify otherwise.
    (6) Replacement of the affected part on an airplane with a part 
listed in table 1 of PAI SB No. 80-0455, constitutes terminating 
action for the repetitive inspections required by this AD for that 
part.
    (7) You may incorporate the actions of PAI SB No. 80-0455, into 
your FAA-approved airplane inspection program (AIP) or maintenance 
program (instructions for continued airworthiness) to ensure the 
continuing airworthiness of each operated airplane.
    (8) After November 16, 2017 (the effective date of this AD), you 
may install on an airplane an affected control surface not listed in 
table 1 of PAI SB No. 80-0455, provided that before further flight 
after installation, the affected control surface has been inspected 
as specified in this AD and found airworthy.

(g) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Standards Office, FAA, has the authority to approve AMOCs for this 
AD, if requested using the procedures found in 14 CFR 39.19. Send 
information to ATTN: Mike Kiesov, Aerospace Engineer, FAA, Small 
Airplane Standards Branch, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4144; fax: (816) 329-4090; 
email: <a href="/cdn-cgi/l/email-protection#2d40444648034644485e425b6d4b4c4c034a425b"><span class="__cf_email__" data-cfemail="036e6a68662d686a66706c75436562622d646c75">[email protected]</span></a>. Before using any approved AMOC on any 
airplane to which the AMOC applies, notify your appropriate 
principal inspector (PI) in the FAA Flight Standards District Office 
(FSDO), or lacking a PI, your local FSDO.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, Small Airplane 
Standards Branch, FAA; or the European Aviation Safety Agency 
(EASA).
    (3) Reporting Requirements: For any reporting requirement in 
this AD, 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.

(h) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) AD No.: 
2017-0045, dated March 9, 2017 for related information. You may 
examine the MCAI on the Internet at https://www.regulations.gov/document?D=FAA-2017-0648-0002.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) PIAGGIO AERO INDUSTRIES S.p.A. Mandatory Service Bulletin 
(SB) No.: 80-0455, dated January 13, 2017.
    (ii) Reserved.
    (3) For PIAGGIO AERO INDUSTRIES S.p.A. service information 
identified in this AD, contact PIAGGIO AERO INDUSTRIES S.p.A.--
Continued Airworthiness, Via Pionieri e Aviatori d'Italia snc--16154 
Genova, Italy; Telephone: +39 010 0998046; Fax: None; email: 
<a href="/cdn-cgi/l/email-protection#57363e25203825233f3e3932242417273e3630303e38363225382427363432793e23"><span class="__cf_email__" data-cfemail="84e5edf6f3ebf6f0ecedeae1f7f7c4f4ede5e3e3edebe5e1f6ebf7f4e5e7e1aaedf0">[email protected]</span></a>; Internet: 
www.piaggioaerospace.it/en/customer-support#care.
    (4) You may view this service information at the FAA, Policy and 
Innovation Division, 901 Locust, Kansas City, Missouri 64106. For 
information on the availability of this material at the FAA, call 
(816) 329-4148. In addition, you can access this service information 
on the Internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2017-0648.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Kansas City, Missouri, on September 29, 2017.
Pat Mullen,
Acting Deputy Director, Policy & Innovation Division, Aircraft 
Certification Service.
[FR Doc. 2017-21443 Filed 10-11-17; 8:45 am]
 BILLING CODE 4910-13-P


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