4056 Federal Register / Vol. 76, No. 15 / Monday, January 24, 2011 / Rules and Regulations 

■ b. In paragraph (a), by removing the 

words ‘‘listed in § 94.6(d)’’ and adding 

the words ‘‘identified in accordance 

with § 94.6(a)(2)’’ in their place. 

Done in Washington, DC this 12th day of 

January 2011. 

Edward M. Avalos, 

Under Secretary for Marketing and Regulatory 

Programs. 

[FR Doc. 2011–1289 Filed 1–21–11; 8:45 am] 

BILLING CODE 3410–34–P 

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. 

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. 


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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

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Functional test of the fuselage 

drain holes.

3 work-hours × $85 per hour = 

$255.

Not applicable ................................ $255 $26,010 

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 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 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 


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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 


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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. 


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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 

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] 


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Federal Register / Vol. 76, No. 15 / Monday, January 24, 2011 / Rules and Regulations 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 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No. 30763; Amdt. No. 3408] 

Standard Instrument Approach 

Procedures, and Takeoff Minimums 

and Obstacle Departure Procedures; 

Miscellaneous Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This establishes, amends, 

suspends, or revokes Standard 

Instrument Approach Procedures 

(SIAPs) and associated Takeoff 

Minimums and Obstacle Departure 

Procedures for operations at certain 

airports. These regulatory actions are 

needed because of the adoption of new 

or revised criteria, or because of changes 

occurring in the National Airspace 

System, such as the commissioning of 

new navigational facilities, adding new 

obstacles, or changing air traffic 

requirements. These changes are 

designed to provide safe and efficient 

use of the navigable airspace and to 

promote safe flight operations under 

instrument flight rules at the affected 

airports. 

DATES: This rule is effective January 24, 

2011. The compliance date for each 

SIAP, associated Takeoff Minimums, 

and ODP is specified in the amendatory 

provisions. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of January 24, 

2011. 

ADDRESSES: Availability of matters 

incorporated by reference in the 

amendment is as follows: 

For Examination— 

1. FAA Rules Docket, FAA 

Headquarters Building, 800 

Independence Avenue, SW., 

Washington, DC 20591; 

2. The FAA Regional Office of the 

region in which the affected airport is 

located; 

3. The National Flight Procedures 

Office, 6500 South MacArthur Blvd., 

Oklahoma City, OK 73169; or 

4. 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Availability—All SIAPs and Takeoff 

Minimums and ODPs are available 

online free of charge. Visit http:// 

www.nfdc.faa.gov to register. 

Additionally, individual SIAP and 

Takeoff Minimums and ODP copies may 

be obtained from: 


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