Document ID: FAA-2011-0054-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 airplanes
Posted Date: 2011-01-24T05:00Z

[Federal Register: January 24, 2011 (Volume 76, Number 15)]
[Rules and Regulations]               
[Page 4056-4061]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr24ja11-3]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0054; Directorate Identifier 2010-CE-070-AD; 
Amendment 39-16582; AD 2011-01-53]
RIN 2120-AA64

 
Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model 
PIAGGIO P-180 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 the 
products listed above. This emergency AD was sent previously to all 
known U.S. owners and operators of these airplanes. This AD supersedes 
Emergency AD 2011-01-51, requires an immediate functional test of the 
fuselage drain holes, and requires sending a report of the results to 
the FAA. This AD also allows, with noted exceptions, for the return/
position of the airplane to a home base, hangar, maintenance facility, 
etc. This AD was prompted by reports of water accumulation in the belly 
of the fuselage that froze and caused the flight controls to jam. We 
are issuing this AD to prevent water or fluid from accumulating in the 
belly of the fuselage and freezing when the aircraft reaches and holds 
altitudes where the temperature is below the freezing point. This 
condition could cause the flight controls to jam with consequent loss 
of control.

DATES: This AD is effective January 24, 2011 to all persons except 
those persons to whom it was made immediately effective by Emergency AD 
2011-01-53, issued on December 20, 2010, which contained the 
requirements of this amendment.
    We must receive comments on this AD by March 10, 2011.

ADDRESSES: You may send comments 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: Deliver to Mail address above 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; 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 AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations 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 Kiesov, Aerospace Engineer, Small 
Airplane Directorate, FAA, 901 Locust, Kansas City, MO 64106; phone: 
(816) 329-4144; fax: (816) 329-4090; e-mail: mike.kiesov@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, is considered 
the State of Design for PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-
180 airplanes. A reported occurrence of the flight controls jamming on 
a Model PIAGGIO P-180 airplane prompted EASA to issue AD No. 2007-0025, 
dated February 1, 2007. This prompted the FAA to issue AD 2007-24-15, 
Amendment 39-15281 (72 FR 67843, December 3, 2007). AD 2007-24-15 
requires correcting the fuselage drain system and ensuring that the 
drain lines of the environmental unit condenser are not clogged.
    Since AD 2007-24-15 became effective, we received reports of two 
additional incidences of water accumulating in the belly of the 
fuselage that froze and caused the flight controls to jam on Model 
PIAGGIO P-180 airplanes. These reports prompted us to issue Emergency 
AD 2011-01-51 on December 18, 2010, to require an immediate functional 
test of the fuselage drain holes and submitting a report of the results 
to the FAA. It also allows, with noted exceptions, for the return/
position of the airplane to a home base, hangar, maintenance facility, 
etc.
    After we issued Emergency AD 2011-01-51, we realized that we 
inadvertently omitted figure 2 in Appendix 1. This prompted us to 
supersede Emergency AD 2011-01-51 and issue Emergency AD 2011-01-53.
    This condition, if not corrected, could result in water or fluid 
accumulating in the belly of the fuselage and freezing when the 
aircraft reaches and holds altitudes where the temperature is below the 
freezing point, which could cause the flight controls to jam with 
consequent loss of 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 the same type design.

AD Requirements

    We are superseding Emergency AD 2011-01-51 with a new AD, which was 
issued as Emergency AD 2011-01-53 on December 20, 2010. This AD retains 
the actions from Emergency AD 2011-01-51, adds figure 2 to Appendix 1, 
and corrects other minor typographical errors.

Interim Action

    We consider this AD interim action. The FAA is working with EASA 
and PIAGGIO on this unsafe condition. Due to the nature of the 
immediate safety of flight situation, the FAA is working this AD 
concurrently with EASA instead of waiting for EASA, as the State of 
Design, to issue an AD. Thus, this action is considered unilateral AD 
action.

FAA's 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 water 
or fluid accumulating in the belly of the fuselage and freezing could 
cause the flight controls to jam with consequent 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.

[[Page 4057]]

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-2011-0054 and 
Directorate Identifier 2010-CE-070-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 102 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
----------------------------------------------------------------------------------------------------------------
Functional test of the fuselage     3 work-hours x $85    Not applicable......            $255          $26,010
 drain holes.                        per hour = $255.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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, 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):

2011-01-53 PIAGGIO AERO INDUSTRIES S.p.A: Amendment 39-16582; Docket 
No. FAA-2011-0054; Directorate Identifier 2010-CE-070-AD.

Effective Date

    (a) This AD is effective January 24, 2011 to all persons except 
those persons to whom it was made immediately effective by Emergency 
AD 2011-01-53, issued on December 20, 2010, which contains the 
requirements of this amendment.

Affected ADs

    (b) This AD supersedes Emergency AD 2011-01-51, issued December 
18, 2010, which was sent to owners/operators of PIAGGIO AERO 
INDUSTRIES S.p.A Model PIAGGIO P-180 airplanes. AD 2007-24-15, 
Amendment 39-15281 (72 FR 67843, December 3, 2007) is related to 
this subject and remains in effect.

Applicability

    (c) This AD applies to PIAGGIO AERO INDUSTRIES S.p.A Model 
PIAGGIO P-180 airplanes, all serial numbers, certified in any 
category.

Subject

    (d) Joint Aircraft System Component (JASC)/Air Transport 
Association (ATA) of America Code 53, Fuselage.

Unsafe Condition

    (e) This AD was prompted by reports of water accumulation in the 
belly of the fuselage that froze and caused the flight controls to 
jam. We are issuing this AD to prevent water or fluid from 
accumulating in the belly of the fuselage and freezing when the 
aircraft reaches and holds altitudes where the temperature is below 
the freezing point. This condition could cause the flight controls 
to jam, which could result in loss of control.

Compliance

    (f) Comply with this AD within the compliance times specified.

Inspection and Corrective Actions

    (g) Unless already done in compliance with Emergency AD 2011-01-
51, before further flight, do the following actions using the 
instructions in Appendix 1 of this AD.
    (1) Remove the central floor panels in the cabin and inspect the 
fuselage belly; and
    (2) Functional test the fuselage drain holes.

Reporting Requirement

    (h) Unless already done, within 24 hours after complying with 
the actions required in paragraph (g) of this AD, fill out the 
reporting form provided in Appendix 2 of this AD and send to the FAA 
at the address (facsimile, e-mail) referenced in the Related 
Information section, paragraph (l) of this AD.
    (i) For the 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

[[Page 4058]]

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.

Provision to Return to Home Base

    (j) For the actions required in paragraph (g) of this AD, you 
may return/position the airplane to a home base, hangar, maintenance 
facility, etc., provided the following are adhered to:
    (1) A water drain hole test is done immediately before the 
repositioning flight and the airplane passes this test. The 
instructions for this test are included in Appendix 3 of this AD. If 
the airplane does not pass this test, then the actions of paragraph 
(g) of this AD must be done without a repositioning flight, unless a 
special flight permit is granted;
    (2) This repositioning flight does not exceed a total of 5 hours 
time-in-service; and
    (3) Use of autopilot is prohibited.

Alternative Methods of Compliance (AMOCs)

    (k)(1) The Manager, Standards Office, Small Airplane 
Directorate, 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 Standards Office, send it 
to the attention of the person identified in the Related Information 
section of this AD.
    (2) Accomplishment of Piaggio Service Bulletin (ALERT) No. 80-
0234, dated December 20, 2010, in its entirety provides an 
acceptable level of safety to the actions of this AD and thus is 
considered an approved AMOC for AD 2011-01-53.
    (3) Before using any approved AMOC, notify your Principal 
Maintenance Inspector or Principal Avionics Inspector, as 
appropriate, or lacking a principal inspector, your local Flight 
Standards District Office.

Related Information

    (l) For further information about this AD, contact Mike Kiesov, 
Aerospace Engineer, Small Airplane Directorate, FAA, 901 Locust, 
Kansas City, MO 64106; phone: (816) 329-4144; fax: (816) 329-4090; 
e-mail: mike.kiesov@faa.gov.

Appendix 1 to AD 2011-01-53

Functional Test of the Fuselage Drain Holes

    1. Remove the electrical power (Ref. AMM Chapter 24-00-00).
    2. Remove the carpet from the aisle in the passenger 
compartment: The carpet is installed on the aircraft with Velcro; 
remove it by hand.
    3. Remove the aisle floor panels 231 ALF, 231 FLF, 231 MLF, and 
231 QLF (Ref. AMM Chapter 06-00-00).
    4. Inspect the fuselage belly for presence of fluid or ice. 
Inspect the lateral bays through the lightening holes.
    a. If fluid is found in the belly, drain it and collect. Take 
note of the amount of fluid removed from the belly, and in which bay 
the fluid was trapped.
    b. If ice is found in the belly, thaw it, then drain and 
collect. Take note of the amount of fluid removed from the belly, 
and in which bay the ice was trapped.
    NOTE: BEFORE THAWING THE ICE, PUT A SUITABLE CONTAINER BELOW THE 
EXTERNAL DRAIN HOLES TO COLLECT THE FLUID.
    c. Evaluate the amount of fluid collected:
    i. If water is found only in the bottom of the belly (i.e., 
undrainable within the keel beams), go to step 6. Step 5 does not 
need to be accomplished at this time.
    ii. If water is found in excess of item above (4-c-i), do step 
5.
    5. Add 6.3 mm draining holes as per attached figure 1 
(additional drain holes on keel beam webs) connecting the lateral 
bays to the center ones or, as alternative, apply Piaggio Aero 
Industries Service Bulletin 80-0291. Then proceed with step 6.
    6. Inspect the fuselage belly for presence of dirt/debris. Take 
note of dirt/debris found and of its location (which bay).
    7. Inspect the fuselage belly for signs of previous fluid 
pooling (waterlines or similar). Take note of any sign found.
    8. Inspect the six (6) flapper valves (two near FR 20, FR 32, 
and FR 36) to verify if they are clogged, stuck to the fuselage 
skin, or laying against the skin for their entire length.
    a. Clean any clogged flapper valve. Take note of any clogged 
flapper valve and its position.
    b. Carefully free any stuck flapper valve. Take note of any 
stuck flapper valve and its position.
    c. If--after cleaning and repositioning--the rubber flap is 
still laying against the skin for its entire length, cut off the 
rubber flap. Replace it at the next A check.
    9. Inspect the six (6) external drain holes:
    a. Verify if they are clogged. If any drain hole is clogged, 
clean it.
    b. Check for proper dimension (3.2 mm). Rework to nominal 
dimension any external drain hole that is found undersized. Protect 
the reworked drain hole by means of Alodyne. Take note of any drain 
hole found clogged and/or reworked, and its position.

Appendix 1 to AD 2011-01-53 (Continued)

Functional Test of the Fuselage Drain Holes

BILLING CODE 4910-13-P

[[Page 4059]]

[GRAPHIC] [TIFF OMITTED] TR24JA11.000

BILLING CODE 4910-13-C

Appendix 1 to AD 2011-01-53 (Continued)

Functional Test of the Fuselage Drain Holes

    10. Clean the fuselage belly, removing debris. A vacuum cleaner 
may be used.
    11. If possible, identify clues of potential source of fluid, 
such as wet carpets, blue lavatory water, etc.
    12. Test the valves and drain holes as described:
    a. Place an adequate amount of water in each bay between FR 19 
and FR 36 (See figure 2) to verify that the water is conveyed in the 
central bays and that it is drained. Use at least \1/2\ gallon 
(approximately 2 liters).
    NOTE: TAKE CARE NOT TO COME IN CONTACT WITH ELECTRICAL 
CONNECTORS WHILE POURING WATER.
    b. A steady stream of water should be observed coming from the 
external drain holes. If not, the flapper valve does not drain 
properly. Cut off the rubber flap and replace the flapper valve at 
next A check. Take note of any cut rubber flap and its position.
    13. Dry the fuselage belly.
    14. Install the aisle floor panels 231ALF, 231 FLF, 231 MLF, and 
231 QLF (Ref. AMM Chapter 06-00-00).
    15. Re-install the carpet:
    a. Make sure that the floor is clean and free of objects.
    b. Make sure that the Velcro is well fixed and cleaned.
    c. Put the carpet in position on the floor and fix it with the 
Velcro.
    16. Collect information on total time flown in the last 6 
months. Specify if the aircraft was exposed to heavy rain conditions 
while parked or during flights.

[[Page 4060]]

    17. Make an appropriate entry in the airplane logbook to show 
compliance with this emergency AD.
BILLING CODE 4910-13-P

Appendix 1 to AD 2011-01-53 (Continued)

Functional Test of the Fuselage Drain Holes
[GRAPHIC] [TIFF OMITTED] TR24JA11.001

BILLING CODE 4910-13-C

Appendix 2 to AD 2011-01-53 Reporting Form

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

------------------------------------------------------------------------
AIC S/N:                 A/C Flight Hours:        A/C Registration:
------------------------------------------------------------------------

------------------------------------------------------------------------
Step 4a--water collected in the belly    If YES, specify amount and
                                          location:
[YES] [NO]
------------------------------------------------------------------------
Step 4b--ice collected in the belly      If YES, specify amount and
                                          location:
[YES] [NO]
------------------------------------------------------------------------

[[Page 4061]]

Step 5--added drain holes                If YES, specify work performed:
[YES] [NO]
------------------------------------------------------------------------
Step 6--debris/dirt in the belly         If YES, specify amount and
                                          location:
[YES] [NO]
------------------------------------------------------------------------
Step 7--signs of previous fluid pooling  If YES, specify amount and
                                          location:
[YES] [NO]
------------------------------------------------------------------------
Step 8--flapper valves inspection        Specify, if any, which flapper
                                          valve was found clogged or
                                          stuck and, if any, which
                                          rubber flap was cut off.

------------------------------------------------------------------------
Step 9--drain holes inspection           Specify, if any, which drain
                                          hole was found clogged.
                                         Specify, if any, which drain
                                          hole was found undersized.

------------------------------------------------------------------------
Step 11--clues of potential source of
 fluid.

------------------------------------------------------------------------
Step 12--drain test                      Specify, if any, which flapper
                                          valve does not have a steady
                                          stream of water.
------------------------------------------------------------------------
Step 16--Total time flown in the last 6
 months. Specify if the aircraft was
 exposed to heavy rain conditions while
 parked or during flights.
------------------------------------------------------------------------
Date:                                    Accomplished by:
------------------------------------------------------------------------
Signature
------------------------------------------------------------------------
                             Send Report to:
  Mike Kiesov, Aerospace Engineer, Small Airplane Directorate, FAA, 901
                     Locust, Kansas City, MO 64106;
phone: (816) 329-4144; fax: (816) 329-4090; e-mail: mike.kiesov@faa.gov.
------------------------------------------------------------------------

Appendix 3 to AD 2011-01-53 Water Drain Hole Test

    1. Put a container under the fuselage external drain holes.
    2. Insert a plastic or wooden stick (or similar tool), minimum 
length 3 inches (7.5 cm), diameter 0.1 inch (2.5 mm) in each of the 
6 fuselage external drain holes.
    3. Verify the stick may enter freely in the drain hole.
    4. If the stick does not enter freely, repositioning flight is 
not allowed.
    5. If more than 1 cup (250 ml) of water is drained from 2 drain 
holes at each station while inserting the stick, repositioning 
flight is not allowed.

    Issued in Kansas City, Missouri, on January 13, 2011.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011-1136 Filed 1-21-11; 8:45 am]
BILLING CODE 4910-13-P