Federal Register / Vol. 77, No. 159 / Thursday, August 16, 2012 / Proposed Rules 49389 

(i) Exceptions 

(1) Oxygen containers Type I that have 

been modified in accordance with the 

Accomplishment Instructions of B/E 

Aerospace Service Bulletin 1XCXX–0100– 

35–005, Revision 1, dated December 15, 

2012; and oxygen containers Type II that 

have been modified in accordance with the 

Accomplishment Instructions of B/E 

Aerospace Service Bulletin 22CXX–0100–35– 

003, Revision 1, dated December 20, 2011; 

are compliant with the requirements of 

paragraph (h) of this AD. 

(2) Airplanes on which Airbus 

modification 150703 or Airbus modification 

150704 have not been embodied in 

production do not have to comply with the 

requirements of paragraph (h) of this AD, 

unless an oxygen container has been replaced 

since the airplane’s entry into service. 

(3) Airplanes on which Airbus 

modification 150703 or Airbus modification 

150704 have been embodied in production 

and which are not listed by model and MSN 

in Airbus Service Bulletin A320–35A1047, 

dated March 29, 2011, are not subject to the 

requirements of paragraphs (g) and (h) of this 

AD, unless an oxygen container has been 

replaced since the airplane’s entry into 

service. 

(4) Model A319 airplanes that are equipped 

with a gaseous oxygen system for passengers, 

installed in production with Airbus 

modification 33125, do not have the affected 

passenger oxygen containers installed. 

Unless these airplanes have been modified 

in-service (no approved Airbus modification 

exists), the requirements of paragraphs (g) 

and (h) of this AD do not apply to these 

airplanes. 

(j) Parts Installation Limitations 

As of the effective date of this AD, no 

person may install an oxygen container 

having a part number specified in table 2 of 

this AD and having a serial number specified 

in table 1 of this AD, on any airplane, unless 

the container has been modified in 

accordance with the Accomplishment 

Instructions of any of the following service 

bulletins; as applicable: 

(1) Airbus Service Bulletin A320–35A1047, 

dated March 29, 2011. 

(2) B/E AEROSPACE Service Bulletin 

1XCXX–0100–35–005, Revision 1, dated 

December 15, 2012. 

(3) B/E AEROSPACE Service Bulletin 

22CXX–0100–35–003, Revision 1, dated 

December 20, 2011. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (h) of this AD, 

if those actions were performed before the 

effective date of this AD using the service 

information specified in paragraph (k)(1) or 

(k)(2) of this AD. 

(1) B/E AEROSPACE Service Bulletin 

1XCXX–0100–35–005, dated March 14, 2011. 

(2) B/E AEROSPACE Service Bulletin 

22CXX–0100–35–003, dated March 17, 2011. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, 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 International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1405; fax (425) 

227–1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

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. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(m) Related Information 

(1) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2011– 

0167, dated September 6, 2011, and the 

service information specified in paragraphs 

(m)(1)(i), (m)(1)(ii), and (m)(1)(iii) of this AD, 

for related information. 

(i) Airbus Service Bulletin A320–35A1047, 

dated March 29, 2011. 

(ii) B/E AEROSPACE Service Bulletin 

1XCXX–0100–35–005, Revision 1, dated 

December 15, 2012. 

(iii) B/E AEROSPACE Service Bulletin 

22CXX–0100–35–003, Revision 1, dated 

December 20, 2011. 

(2) For Airbus service information 

identified in this proposed AD, contact 

Airbus, Airworthiness Office—EAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 96; 

fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; Internet 

http://www.airbus.com. For B/E service 

information identified in this proposed AD, 

contact B/E Aerospace Systems GmbH, 

Revalstrasse 1, 23560 Lubeck, Germany; 

telephone (49) 451 4093–2976; fax (49) 451 

4093–4488. You may review copies of the 

referenced service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on August 

3, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–20112 Filed 8–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0845; Directorate 

Identifier 2012–CE–013–AD] 

RIN 2120–AA64 

Airworthiness Directives; Revo, 

Incorporated Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain Revo, 

Incorporated Models COLONIAL C–1, 

COLONIAL C–2, LAKE LA–4, LAKE 

LA–4A, LAKE LA–4P, and LAKE LA–4– 

200 airplanes. The existing AD currently 

requires a one-time dye-penetrant 

inspection of the horizontal stabilizer 

attachment fitting and repetitive visual 

inspections of the fitting for any 

evidence of fretting, cracking, or 

corrosion (with necessary replacement 

and modification); replacement of the 

fitting upon reaching the 850-hours 

time-in-service (TIS) safe life; and 

reporting to the FAA the results of the 

initial inspection and any cracks found 

on repetitive inspections. Since we 

issued AD 2005–12–02, Revo, 

Incorporated informed the FAA that 

while the drawing numbers are 

different, the attachment fittings on the 

Model COLONIAL C–1 airplanes are 

identical in every other respect to those 

installed on the airplanes referenced in 

AD 2005–12–02. This proposed AD 

would retain the actions required by AD 

2005–12–02, add the Model COLONIAL 

C–1 airplanes to the Applicability, and 

add an optional terminating action for 

the requirements. We are proposing this 

AD to correct the unsafe condition on 

these products. 

DATES: We must receive comments on 

this proposed AD by October 1, 2012. 

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: Deliver to Mail 

address above between 9 a.m. and 5 


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49390 Federal Register / Vol. 77, No. 159 / Thursday, August 16, 2012 / Proposed Rules 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact Revo, Incorporated, 

1396 Grandview Boulevard, Kissimmee, 

FL 34744; telephone: (407) 847–8080; 

email: support@teamlake.com; Lake 

Central Air Services, Muskoka Airport, 

R.R. #1, Gravenhurst, Ontario, Canada 

P1P 1R1; telephone: (705) 687–4343; 

email: akecent@muskoka.com; Internet: 

www.lakecentral.com; and Robert L. 

Copeland, 418B Bartow Municipal 

Airport, Bartow, FL 33830; telephone: 

none; email: none; Internet: none. You 

may review copies of the referenced 

service information at the FAA, Small 

Airplane Directorate, 901 Locust St., 

Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329– 

4148. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://www.regulations.

gov; 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 proposed 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: Hal 

Horsburgh, Aerospace Engineer, Atlanta 

Aicraft Certification Office, FAA, 1701 

Columbia Avenue, College Park, Georgia 

30337; phone: (404) 474–5553; fax: (404) 

474–5606; email: hal.horsburgh@faa.

gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–0845; Directorate Identifier 

2012–CE–013–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

Discussion 

On June 2, 2005, we issued AD 2005– 

12–02, amendment 39–14118 (70 FR 

33820, June 10, 2005), for all Revo, 

Incorporated (Type Certificate 1A13 

formerly held by Colonial Aircraft 

Company, Lake Aircraft Corporation, 

Consolidated Aeronautics, Inc., and 

Global Amphibians LLC) Models 

COLONIAL C–2, LAKE LA–4, LAKE 

LA–4A, LAKE LA–4P, and LAKE LA–4– 

200 airplanes. That AD requires a onetime dye-penetrant inspection of the 

horizontal stabilizer attachment fitting 

and repetitive visual inspections of the 

fitting for any evidence of fretting, 

cracking, or corrosion (with necessary 

replacement and modification); 

replacement of the fitting upon reaching 

the 850-hours TIS safe life; and 

reporting to the FAA the results of the 

initial inspection and any cracks found 

on repetitive inspections. That AD 

resulted from several reports of fatigue 

cracks found in the horizontal stabilizer 

attachment fitting (part number (P/N) 2– 

2200–21) of Model LA–4–200 airplanes 

that were in compliance with AD 98– 

10–12 (63 FR 26964, May 15, 1998). We 

issued that AD to detect, correct, and 

prevent future cracks in the horizontal 

stabilizer attachment fitting, which 

could result in failure of the horizontal 

stabilizer attachment fitting. This failure 

could result in loss of control of the 

airplane. 

Actions Since Existing AD Was Issued 

Since we issued AD 2005–12–02 (70 

FR 33820, June 10, 2005), Revo, 

Incorporated on January 10, 2012, 

informed the FAA that while the 

drawing numbers are different, the 

attachment fittings on the Model 

COLONIAL C–1 airplanes are identical 

in every other respect to those installed 

on the airplanes referenced in AD 2005– 

12–02. 

Also, since we issued AD 2005–12–02 

(70 FR 33820, June 10, 2005), we 

determined that installation of 

Supplemental Type Certificate (STC) 

SA02153NY (part number (P/N) LC– 

2200–21) or STC SA03217AT (P/N 

XLS–2–2200–221L/R) terminates the 

requirements of this AD. The actions 

required in the instructions for 

continued airworthiness for the STCs 

would still apply to airplanes with those 

STCs installed. We propose to include 

installation of STC SA02153NY or STC 

SA03217AT as options to this AD. 

Relevant Service Information 

We reviewed Revo, Inc. Service 

Bulletin B–78 R3, dated January 10, 

2012; Revo, Inc. Service Bulletin B–78 

R2, dated October 26, 2011; and Revo, 

Inc. Service Bulletin B–78, dated April 

3, 1998. The service information 

describes procedures for: 

• Removing the fitting and inspecting 

(both visual and dye penetrant) for 

cracks, fretting, or corrosion; 

• Replacing the attachment fitting 

with a new fitting; 

• Measuring the gap between the 

attachment fitting and the horizontal 

stabilizer skin for proper clearance; and 

• Trimming the stabilizer skin to 

provide proper clearance. 

We reviewed Lake Central Aircraft 

Services Lake Amphibian Stabilizer 

Fitting LC–2200–21 Installation 

Instructions, Rev B, dated August 26, 

2005, and Lake Central Air Services 

Stabilizer Fitting LC–2200–21 

Maintenance Manual Supplement 

Document MS–LC–2200–21, Rev B, 

dated August 26, 2005. The service 

information describes procedures for 

installation of the Lake Central Aircraft 

Services Lake Amphibian stabilizer 

fitting (STC SA02153NY). 

We reviewed XLS Company, LLC 

Report XLS–2–2200–500, Installation 

Instructions and Instructions for 

Continued Airworthiness, Revision B, 

November 18, 2005. The service 

information describes procedures for 

installation of the XLS Co., LLC 

horizontal stabilizer support fitting 

system (STC SA03217AT). 

FAA’s Determination 

We are proposing 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. 

Proposed AD Requirements 

This proposed AD would retain all 

requirements of AD 2005–12–02 (70 FR 

33820, June 10, 2005), add airplanes to 

the Applicability section, and add an 

optional terminating action for the 

requirements of this AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 253 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 


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Federal Register / Vol. 77, No. 159 / Thursday, August 16, 2012 / Proposed Rules 49391 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on 

U.S. operators 

Inspect the horizontal stabilizer attachment fitting ...................... 24 work-hours × $85 per hour 

= $2,040.

Not Applicable $2,040 $516,120 

Measure the gap between the horizontal skin and the horizontal stabilizer attachment fitting; trim the skin to provide 

gap.

1 work-hour × $85 per hour = 

$85.

Not Applicable 85 21,505 

We estimate the following costs to do 

any necessary replacement that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replace the horizontal stabilizer attachment fitting .......... 24 work-hours × $85 per hour = $2,040 .......................... $761 $2,801 

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 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

(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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 

removing airworthiness directive (AD) 

2005–12–02, Amendment 39–10524 (70 

FR 33820, June 10, 2005), and adding 

the following new AD: 

Revo, Incorporated: Docket No. FAA–2012– 

0845; Directorate Identifier 2012–CE– 

013–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by October 1, 2012. 

(b) Affected ADs 

This AD supersedes AD 2005–12–02, 

Amendment 39–10524 (70 FR 33820, June 

10, 2005). 

(c) Applicability 

This AD applies to the following Revo, 

Incorporated Models COLONIAL C–1, 

COLONIAL C–2, LAKE LA–4, LAKE LA–4A, 

LAKE LA–4P, and LAKE LA–4–200 

airplanes, all serial numbers, that are 

certificated in any category, and have 

installed horizontal stabilizer attachment 

fittings part number (P/N) 1–2200–14, 2200– 

14, or 2–2200–21. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 55: Stabilizers. 

(e) Unsafe Condition 

This AD was prompted by information 

from Revo, Incorporated that while the 

drawing numbers are different, the 

attachment fittings on the Model COLONIAL 

C–1 airplanes are identical in every other 

respect to those installed on the airplanes 

referenced in AD 2005–12–02 (70 FR 33820, 

June 10, 2005). We are issuing this AD to 

retain the actions required by AD 2005–12– 

02, add the Model COLONIAL C–1 airplanes 

to the Applicability, and add an optional 

terminating action for the requirements. We 

are adopting this AD to correct the unsafe 

condition on these products. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Dye Penetrant Inspection on the 

Horizontal Stabilizer Attachment Fitting 

(1) For airplanes with less than 825 hours 

time-in-service (TIS) on any horizontal 

stabilizer attachment fitting: Remove the 

horizontal stabilizer attachment (P/N 1– 

2200–14, 2200–14, or 2–2200–21) from the 

airplane and inspect for cracks (using dye 

penetrant), fretting, or corrosion using the 

applicable compliance times stated below. To 

take ‘‘already done’’ credit for this 

inspection, you must have removed the 

horizontal stabilizer attachment from the 

airplane when the inspection was done. 

(i) For COLONIAL C–2, LAKE LA–4, LAKE 

LA–4A, LAKE LA–4P, and LAKE LA–4–200 

airplanes: Within the next 25 hours TIS after 

July 8, 2005 (the effective date of AD 2005– 

12–02 (70 FR 33820, June 10, 2005)). Follow 


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Revo Inc. Service Bulletin B–78 R3, dated 

January 10, 2012; or Revo Inc. Service 

Bulletin B–78 R2, dated April 3, 1998. 

(ii) For COLONIAL C–1 airplanes: Within 

the next 25 hours TIS after the effective date 

of this AD. Follow Revo Inc. Service Bulletin 

B–78 R3, dated January 10, 2012. 

(2) If cracks, fretting, or corrosion is found 

during the inspection required in either 

paragraph (g)(1)(i) or (g)(1)(ii) of this AD, 

before further flight, replace with P/N 2– 

2200–21. P/N 2–2200–21 is an approved 

replacement for P/N 1–2200–14 or 2200–14. 

Follow Revo Inc. Service Bulletin B–78 R3, 

dated January 10, 2012. 

(h) Repetitive Inspections of the Horizontal 

Stabilizer Attachment Fitting 

(1) For all airplanes: After the dyepenetrant inspection required in paragraph 

(g) of this AD or after replacement of the 

fitting, at intervals not to exceed 50 hours TIS 

or 12 months, whichever occurs first, 

repetitively inspect (visual) the horizontal 

stabilizer attachment fitting using the 

following procedures: 

(i) Move the elevator as required to see the 

fitting, ensuring that the aft face of the fitting 

is visible. 

(ii) Clean the fitting. Pay special attention 

to the radius edges of the fitting just outboard 

of the fitting ear. 

(iii) Visually inspect the fitting for cracks 

using a flashlight (a small magnifying glass 

or borescope is recommended). Pay special 

attention again to the radius edges just 

outboard of the fitting ear. Also, inspect as 

far forward on the edge that is possible 

because some cracks progress along the 

forward face of the fitting that is mostly 

hidden by the horizontal stabilizer rear beam. 

(iv) Reference the sketch on page 1 of Revo 

Inc. Service Bulletin B–78 R3, dated January 

10, 2012, to see where the crack is likely to 

begin. 

(2) If any cracks are found during any of 

the inspections required in paragraph (h) of 

this AD, before further flight, replace the 

fitting following Revo Inc. Service Bulletin 

B–78 R3, dated January 10, 2012. 

(i) Replace the Horizontal Stabilizer 

Attachment Fitting 

(1) For COLONIAL C–2, LAKE LA–4, LAKE 

LA–4A, LAKE LA–4P, and LAKE LA–4–200 

airplanes: Before or when the horizontal 

stabilizer attachment fitting accumulates 850 

hours TIS or within 25 hours TIS after July 

8, 2005 (the effective date of AD 2005–12–02 

(70 FR 33820, June 10, 2005)), whichever 

occurs later, and repetitively thereafter at 

intervals not to exceed 850 hours TIS replace 

the horizontal stabilizer attachment fitting P/ 

N 1–2200–14, 2200–14, or 2–2200–21. P/N 2– 

2200–21 is an approved replacement part for 

P/N 1–2200–14 or 2200–14. Follow Revo Inc. 

Service Bulletin B–78 R3, dated January 10, 

2012; or Revo Inc. Service Bulletin B–78 R2, 

dated April 3, 1998. 

(2) For COLONIAL C–1 airplanes: Before or 

when the horizontal stabilizer attachment 

fitting accumulates 850 hours TIS or within 

25 hours TIS after the effective date of this 

AD, whichever occurs later, and repetitively 

thereafter at intervals not to exceed 850 hours 

TIS replace the horizontal stabilizer 

attachment fitting P/N 1–2200–14, 2200–14, 

or 2–2200–21. P/N 2–2200–21 is an approved 

replacement part for P/N 1–2200–14 or 2200– 

14. Follow Revo Inc. Service Bulletin B–78 

R3, dated January 10, 2012. 

(3) For all airplanes: You may at any time 

install the following supplemental type 

certificates (STC) to terminate the 

requirements of this AD; however, the 

actions required by the limitations section in 

the instructions for continued airworthiness 

for the STCs still apply: 

(i) Lake Central Aircraft Services Lake 

Amphibian stabilizer fitting (STC 

SA02153NY) following Lake Central Aircraft 

Services Lake Amphibian Stabilizer Fitting 

LC–2200–21 Installation Instructions, Rev B, 

dated August 26, 2005; and Lake Central Air 

Services Stabilizer Fitting LC–2200–21 

Maintenance Manual Supplement Document 

MS–LC–2200–21, Rev B, dated August 26, 

2005; or 

(ii) XLS Co., LLC horizontal stabilizer 

support fitting system (STC SA03217AT) 

following XLS Company, LLC Report XLS–2– 

2200–500, Installation Instructions and 

Instructions for Continued Airworthiness, 

Revision B, November 18, 2005. 

Note for paragraph (i)(3)(ii) of this AD: 

New parts are not currently available for STC 

SA03217AT; however, the STC number has 

been included here for future reference if the 

parts do become available. 

(4) You may install airworthy horizontal 

stabilizer attachment fitting, P/N 1–2200–14, 

2200–14, or 2–2200–21, provided it has less 

than 850 hours TIS and has been inspected 

following paragraph (g) of this AD and found 

free of cracks, fretting, or corrosion. 

(j) Measure the Gap Between the Horizontal 

Skin and the Horizontal Stabilizer 

Attachment Fitting; Trim the Skin To 

Provide Gap 

(1) For all airplanes: Measure the gap 

between the horizontal skin and the 

horizontal stabilizer attachment fitting (P/N 

1–2200–14, 2200–14, or 2–2200–21). If gap is 

less than 1⁄16-inch, trim the skin to provide 

at least 1⁄16 inch gap. 

(2) Perform the actions in paragraph (j)(1) 

before further flight after any inspection 

required by paragraph (g)(1)(i) or (g)(1)(ii) of 

this AD, or replacement of the fitting 

required by paragraph (g)(2) or (h)(2) of this 

AD. 

(k) Report the Results of the Initial 

Inspection 

For all airplanes: Using the form in 

Appendix 1 of this AD report the results of 

the inspections required in paragraphs (g) 

and (h) of this AD. Send the results to the 

FAA using the following contact information: 

Hal Horsburgh, FAA Atlanta Aircraft 

Certification Office (ACO), 1701 Columbia 

Ave., College Park, GA 30337; fax (404) 474– 

5606; or email: hal.horsburgh@faa.gov. Send 

the results within the following compliance 

times: 

(1) Within 30 days after the inspection 

required in paragraph (g) of this AD even if 

no damage is found. 

(2) Within 30 days after any inspection 

required by paragraph (h) of this AD if cracks 

are found. 

(l) Special Flight Permit 

Special flight permits are allowed for this 

AD with these limitations: 

(1) Vne reduced to 121 m.p.h. (105 knots); 

and 

(2) No flight into known turbulence. 

(m) 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. 

(n) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta 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 the 

Related Information section 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. 

(3) AMOCs approved for AD 2005–12–02 

(70 FR 33820, June 10, 2005) are approved as 

AMOCs for this AD. 

(o) Related Information 

(1) For more information about this AD, 

contact Hal Horsburgh, Aerospace Engineer, 

Atlanta ACO, FAA, 1701 Columbia Avenue, 

College Park, Georgia 30337; phone: (404) 

474–5553; fax: (404) 474–5606; email: 

hal.horsburgh@faa.gov. 

(2) For service information identified in 

this AD, contact Revo, Incorporated, 1396 

Grandview Boulevard, Kissimmee, FL 34744; 

telephone: (407) 847–8080; email: 

support@teamlake.com; Internet: none; Lake 

Central Air Services, Muskoka Airport, R. R. 

#1, Gravenhurst, Ontario, Canada P1P 1R1; 

telephone: (705) 687–4343; email: 

akecent@muskoka.com; Internet: 

www.lakecentral.com; and Robert L. 

Copeland, 418B Bartow Municipal Airport, 

Bartow, FL 33830; telephone: none; email: 

none; Internet: none. You may review copies 

of the referenced service information at the 

FAA, Small Airplane Directorate, 901 Locust 

St., Kansas City, Missouri 64106. For 


wreier-aviles on DSK7SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 159 / Thursday, August 16, 2012 / Proposed Rules 49393 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

Appendix 1 to Docket No. FAA–2012– 

0845 

INSPECTION REPORT for Revo, 

Incorporated Models COLONIAL C–1, 

COLONIAL C–2, LAKE LA–4, LAKE LA–4A, 

LAKE LA–4P, and LAKE LA–4–200 

Airplanes 

BILLING CODE 4910–13–P 


wreier-aviles on DSK7SPTVN1PROD with PROPOSALSEP16AU12.034</GPH>
49394 Federal Register / Vol. 77, No. 159 / Thursday, August 16, 2012 / Proposed Rules 

Issued in Kansas City, Missouri, on August 

9, 2012. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–20107 Filed 8–15–12; 8:45 am] 

BILLING CODE 4910–13–C 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0806; Directorate 

Identifier 2012–NM–022–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model DHC–8–400, 

–401, and –402 airplanes. This proposed 

AD was prompted by reports of an inservice incident where the propeller deicing system became unavailable due to 

burnt/chafed wires within the 

alternating current contractor box 

(ACCB). This proposed AD would 

require inspection for chafing, damage, 

and loose wiring within an ACCB and 

repair if necessary; and would require 

rework and re-identification of the 

wiring installation within each ACCB. 

We are proposing this AD to detect and 

correct damaged, chafed, or loose wiring 

within an ACCB, which could affect the 

operation of the windshield heater, ice 

detector, angle of attack (AOA) vane 

heater, pilot probe heater, engine intake 

heater, or propeller de-icing system, and 

subsequently adversely affect the 

airplane’s flight characteristics in icing 

conditions. 

DATES: We must receive comments on 

this proposed AD by October 1, 2012. 

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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Bombardier, 

Inc., Q–Series Technical Help Desk, 123 

Garratt Boulevard, Toronto, Ontario 

M3K 1Y5, Canada; telephone 416–375– 

4000; fax 416–375–4539; email 

thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. 

You may review copies of the 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Assata Dessaline, Aerospace Engineer, 

Avionics and Flight Test Branch, ANE– 

172, FAA, New York Aircraft 

Certification Office (ACO), 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7301; fax 

(516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–0806; Directorate Identifier 

2012–NM–022–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on 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 proposed AD. 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2012–03, 

dated January 11, 2012 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

There has been one (1) reported in-service 

incident where the propeller de-icing system 

became unavailable due to burnt/chafed 

wires within the Alternating Current 

Contactor Box (ACCB). There has also been 

a number of additional minor events of wires 

found chafed within ACCBs. 

An investigation revealed that inadequate 

clearance between the wires and metallic 

structure within the ACCB could cause 

chafed wires. 

Damaged, chafed or loose wiring within an 

ACCB could affect the operation of the 

windshield heater, ice detector, angle of 

attack (AOA) vane heater, pitot probe heater, 

engine intake heater or propeller de-icing 

system. Loss of one of these systems could 

adversely affect the aeroplane’s flight 

characteristics in icing conditions. 

This [TCCA] Airworthiness Directive (AD) 

mandates the [visual] inspection [for 

damaged, chafed, and loose wiring within an 

ACCB and replace if necessary] and 

rectification [rework] of the wiring 

installation within each ACCB. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Bombardier, Inc. has issued the 

following service bulletins: 

• Bombardier Service Bulletin 84–24– 

47, Revision A, dated September 14, 

2011. 

• Bombardier Service Bulletin 84–24– 

48, Revision A, dated September 14, 

2011. 

• Bombardier Service Bulletin 84–24– 

49, Revision A, dated September 14, 

2011. 

• Bombardier Service Bulletin 84–24– 

50, Revision A, dated September 14, 

2011. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 


wreier-aviles on DSK7SPTVN1PROD with PROPOSALS