AD 2011-01-51

FAA Aviation Safety EMERGENCY AIRWORTHINESS DIRECTIVE www.faa.gov/aircraft/safety/alerts/

DATE: December 17, 2010 AD #: 2011-01-51 Background This emergency AD was prompted by three incidents of the flight controls jamming on Piaggio Model P-80 airplanes.

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 the Piaggio Model P-180 airplanes. One of the reported occurrences prompted EASA to issue AD No. 2007-0025, dated February 1, 2007, and the FAA followed with AD 2007-24-15, Amendment 39-15321 (72 FR 67843, December 3, 2007). That AD required correcting the fuselage drain system and ensuring that the drain lines of the environmental unit condenser were not clogged. Since AD 2007-24-15 became effective, the FAA has received information on two additional incidences where Piaggio Model P-180 airplanes encountered water accumulation in the belly of the fuselage that froze and caused the flight controls to jam. The FAA is working with EASA and Piaggio on this issue. 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 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 an immediate functional test of the fuselage drain holes and a report of the results to the FAA. It also allows for the return/position the airplane to a home base, hangar, maintenance facility, etc. Interim Action We consider this AD interim action. 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 1

with prom oting 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. Presentation of the Actual AD We are issuing this AD under 49 U.S.C. Section 44701 according to the authority delegated to me by the Administrator. 2011-01-51 Piaggio Aero Industries S.p.A (Piaggio): Directorate Identifier 2010-CE-069-AD. Effective Date (a) This Emergency AD is effective upon receipt. Affected ADs (b) This AD does not supersede or revise any AD. AD 2007-24-15, Amendment 39-15321 (72 FR 67843, December 3, 2007) is related to this subject and remains in effect. Applicability (c) This AD applies to Piaggio Model 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 emergency AD was prompted by three incidents of the flight controls jamming on Piaggio Model P-180 airplanes. This condition, if not corrected, could result in water or fluid accumulating and freezing when the aircraft reaches and holds altitudes where the temperature is below the freezing point. If not corrected, this may cause the flight controls to jam and result in loss of control. Compliance (f) Unless already done within the last 24 hours after receipt of this emergency AD, before further flight, perform the following actions using the instructions in Appendix 1 of this AD. (1) Removal of central floor panels in the cabin and inspection of fuselage belly; and (2) Functional test of the fuselage drain holes. (g) Within 24 hours after complying with the actions required in paragraph (f) of this AD, fill out the reporting form provided in Appendix 2 of this AD and send to the FAA at the address (facsimile, email) referenced in the Related Information section, paragraph (k) of this AD. 2

Provision to Return to Home Base (h) For the actions of paragraph (f) of this AD, you m ay 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 (f) 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 (TIS); and (3) Use of autopilot is prohibited.

Reporting Requirement

(i) 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. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, Standards Staff, 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 Staff, send it to the attention of the person identified in the Related Information section of this AD. (2) 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 (k) For further information about this AD, contact one of the following: (1) Sarjapur Nagarajan, Aerospace Engineer, Small Airplane Directorate, FAA, 901 Locust, Kansas City, MO 64106; phone: (816) 329-4145; fax: (816) 329-4090; e-mail: sarjapur.nagarajan@faa.gov. (2) Peter Rouse, Aerospace Engineer, Small Airplane Directorate, FAA, 901 Locust, Kansas City, MO 64106; phone: (816) 329-4135; fax: (816) 329-4090; e-mail: peter.rouse@faa.gov. (3) 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. 3

Appendix 1 to Emergency AD 2011-01-26 Functional Test of the Fuselage Drain Holes

1. Rem ove 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, 231 QLF (Ref. AMM Chapter 06-00- 00). 4. Inspect the fuselage belly for pr esence of fluid or ice. Inspect also the lateral bays through the lightening holes. a. If fluid is found in the belly, drai n 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 drai n 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, PU T 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., undrainabl e 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), perform step 5 5. Add 6.3 mm draining holes as per attached figur e 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. 4

Appendix 1 to Emergency AD 2011-01-26 (Continued) Functional Test of the Fuselage Drain Holes STA STA STA STA SȚA STA STA 4762 4968 5174 5380 5586 5792 5000 ++++++ +)A 7I++++ ADDITIONAL DRAIN HOLES KEEL BEAM WEB Ø 6.3 mm ADDITIONAL HOLE TYPICAL SECTION A-A APPLICABLE TO FRAMES: - FROH # 20 TO # 31 - FROM # 32 TO # 35 SKIN Fig 1 - Additional drain holes on keel beam webs 5

Appendix 1 to Emergency AD 2011-01-26 (Continued) Functional Test of the Fuselage Drain Holes 6. Inspect the fuselage belly for pres ence of dirt / debris. Take note of dirt / debris f ound, 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 fl ap 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 of its position. 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. Make a test of “valves and drain holes” as described: a. Place an adequate amount of water in each ba y between FR 19 and FR 36 (SEE FIG 2 attached) to verify that the water is conveyed in the central bays and that is drained. At least one half US Gal / approximately 2 liters may be used. NOTE: TAKE CARE NOT TO COME IN CONTACT WITH ELECTRICAL CONNECTORS WHILE POURING WATER. b. Steady stream of water should be observed coming from the exte rnal drain holes . If not, the flapper valve does not drain properly. Cut off the rubber flap, then replace the flapper valve at next A check. Take note of any cut rubber flap and its position. c. Steady stream of water should be observed coming from the exte rnal drain holes . If not, the flapper valve does not drain properly. Cut off the rubber flap, then 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, 231 QLF (Ref. AMM Chapter 06-00-00) 15. Re-install th e 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 6

Appendix 1 to Emergency AD 2011-01-26 (Continued) Functional Test of the Fuselage Drain Holes

16. Collect inform ation on total time flow n in the last 6 months. Specify if the aircraft was exposed to heavy rain condition while parked or during flights. 17. Complete the attached Confirmation Slip and send it back to Piaggio Aero Industries S.p.A. – Product Support Department. 18. Make an appropriate entry in the airplane logbook to show compliance with this Service Bulletin 7

Appendix 2 to Emergency AD 2011-01-51 Reporting Form

A/C S/N: A/C Flight Hours: A/C Registration: Step 4a – water collected in the belly [YES] [NO] If YES, specify amount and location Step 4b – ice collected in the belly [YES] [NO] If YES, specify amount and location Step 5 – added drain holes [YES] [NO] If YES, specify work performed Step 6 – debris / dirt in the belly [YES] [NO] If YES, specify amount and location Step 7 – signs of previous fluid pooling [YES] [NO] If YES, specify amount and location Step 8 – flapper valves inspection Specify if any, and which flapper valve was found clogged or stuck, and if any, and which rubber flap was cut off.

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

Step 11 – clues of potential source of fluid.

Step 12 – drain test Specify if any, and which flapper valve has not a steady stream of water

Step 16 – Total time flown in the last 6 months. Specify if the aircraft was exposed to heavy rain condition while parked or during flights.

8

Appendix 2 to Emergency AD 2011-01-51 (Continued) Reporting Form

Date: Accom plished by: Signature 9

Appendix 3

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 7.5 cm / 3 in, diameter 2.5 mm / 0.1 in 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 250 ml / 1 cup of water is drained from 2 drain holes at each station while inserting the stick, repositioning flight is not allowed. 10

11 Issued in Kansas City, Missouri, on December 18, 2010.

Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service.