This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

45979 

Vol. 77, No. 149 

Thursday, August 2, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0731; Directorate 

Identifier 2012–CE–020–AD] 

RIN 2120–AA64 

Airworthiness Directives; Piper 

Aircraft, 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 

Piper Aircraft, Inc. (type certificate 

previously held by The New Piper 

Aircraft Inc.) PA–28, PA–32, PA–34, 

and PA–44 airplanes. This proposed AD 

was prompted by reports of control 

cable assembly failures that may lead to 

failure of the horizontal stabilator 

control system and could result in loss 

of pitch control. This proposed AD 

would require inspections of the 

stabilator control system and 

replacement of parts as necessary. We 

are proposing this AD to correct the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by September 17, 

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 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Piper 

Aircraft, Inc., 2926 Piper Drive, Vero 

Beach, Florida 32960; telephone: (772) 

567–4361; Internet: www.piper.com. 

You may review copies of the 

referenced service information at the 

FAA, Small Airplane Directorate, 901 

Locust, 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: 

Hector Hernandez, Aerospace Engineer, 

FAA, Atlanta Aircraft Certification 

Office, 1701 Columbia Avenue, College 

Park, Georgia 30337; telephone: (404) 

474–5587; fax: (404) 474–5606; email: 

hector.hernandez@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2012–0731; Directorate Identifier 2012– 

CE–020–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 

We received reports of control cable 

assembly failures that may lead to 

failure of the horizontal stabilator 

control system on Piper PA–28, PA–32, 

PA–34, and PA–44 airplanes. We have 

had reports of cracks, corrosion, failure 

of the turnbuckle, control cable fraying, 

the cable swage end broken and the 

system being held together by 

turnbuckle safety wire. In one report, an 

elevator cable was found broken at the 

terminal end near the turnbuckle, and, 

in another report, the elevator cable 

failed at the fitting that treads into the 

turnbuckle. This condition, if not 

corrected, could result in failure of the 

horizontal stabilator control system with 

subsequent loss of pitch control. 

Relevant Service Information 

We reviewed Piper Aircraft, Inc. 

Mandatory Service Bulletin No. 1245, 

dated May 3, 2012. That service 

information describes procedures for 

inspections of the stabilator control 

system. 

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 require 

inspections of the stabilator control 

system and replacement of parts as 

necessary. We are proposing this AD to 

correct the unsafe condition on these 

products. 

Costs of Compliance 

We estimate that this proposed AD 

affects 34,013 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
45980 Federal Register / Vol. 77, No. 149 / Thursday, August 2, 2012 / Proposed Rules 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection of the horizontal stabilator control system.5 work-hours × $85 per hour = $425 ......... Not applicable ........ $425 $14,455,525 

We estimate the following costs to do 

any necessary replacements 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 

Replacement of all stabilator control cable system— 

per set of cables.

10 work-hours × $85 per hour = $850 ......................... $608 $1,458 

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 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 this 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 adding 

the following new airworthiness 

directive (AD): 

Piper Aircraft, Inc.: Docket No. FAA–2012– 

0731; Directorate Identifier 2012–CE– 

020–AD. 

(a) Comments Due Date 

We must receive comments by September 

17, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Model PA–28–236, PA– 

28–140, PA–28–150, PA–28–151, PA–28– 

160, PA–28–161, PA–28–180, PA–28–181, 

PA–28–201T, PA–28R–201, PA–28–235, PA– 

28R–201T, PA–28S–160, PA–28S–180, PA– 

28R–180, PA–28R–200, PA–28RT–201, PA– 

28RT–201T, PA–32–260, PA–32–301, PA– 

32–301T, PA–32–300, PA–32R–300, PA– 

32R–301T, PA–32R–301 (SP), PA–32R–301 

(HP), PA–32RT–300, PA–32RT–300T, PA– 

32S–300, PA–32–301FT, PA–32–301XTC, 

PA–34–200, PA–34–200T, PA–34–220T, PA– 

44–180, and PA–44–180T airplanes, all serial 

numbers, certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 2740, Stabilizer Control System. 

(e) Unsafe Condition 

This AD was prompted by reports of 

control cable assembly failures that may lead 

to failure of the horizontal stabilator control 

system and could result in loss of pitch 

control. This proposed AD would require 

inspections of the stabilator control system 

and replacement of parts as necessary. We 

are issuing 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) Inspection 

(1) As of the effective date of this AD, if 

the age of the airplane is at or exceeds 15 

years, then at the next annual inspection or 

within the next 12 months after the effective 

date of this AD, whichever occurs later, do 

an initial inspection of the stabilator control 

system following instructions 1 through 10 of 

Piper Aircraft, Inc. Mandatory Service 

Bulletin No. 1245, dated May 3, 2012. 

(2) As of the effective date of this AD, if 

the age of the airplane is less than 15 years, 

then, upon the age of the airplane reaching 

15 years, at the next annual inspection or 

within the next 12 months after the effective 

date of this AD, whichever occurs later, do 

an initial inspection of the stabilator control 

system following instructions 1 through 10 of 

Piper Aircraft, Inc. Mandatory Service 

Bulletin No. 1245, dated May 3, 2012. 

(3) As of the effective date of this AD, if 

the age of the airplane cannot be determined, 

then at the next annual inspection or within 

the next 12 months after the effective date of 

this AD, whichever occurs later, do an initial 

inspection of the stabilator control system 

following instructions 1 through 10 of Piper 

Aircraft, Inc. Mandatory Service Bulletin No. 

1245, dated May 3, 2012. 

Note for paragraph (g)(1), (g)(2) and (g)(3) 

of this AD: To assist in determining the age 

of the airplane, you may contact Piper 

Aircraft, Inc., 2926 Piper Drive, Vero Beach, 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 149 / Thursday, August 2, 2012 / Proposed Rules 45981 

Florida 32960; telephone: (772) 567–4361; 

Internet: www.piper.com; or access the FAA 

airplane registry database at: http:// 

registry.faa.gov/aircraftinquiry/ 

Serial_Inquiry.aspx. 

(4) After the applicable initial inspection 

required in paragraph (g)(1), (g)(2) or (g)(3) of 

this AD, repetitively thereafter at intervals 

not to exceed 2,000 hours time-in-service or 

7 years, whichever occurs first, inspect the 

stabilator control system following 

instructions 1 through 10 of Piper Aircraft, 

Inc. Mandatory Service Bulletin No. 1245, 

dated May 3, 2012. 

(h) Repair 

If any cracks, corrosion, or cable fraying are 

found during any inspection required in 

paragraphs (g)(1), (g)(2), (g)(3) or (g)(4) of this 

AD, before further flight, replace the 

damaged part with an airworthy part. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta Aircraft 

Certification Office (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. 

(j) Related Information 

(1) For more information about this AD, 

contact Hector Hernandez, Aerospace 

Engineer, FAA, Atlanta ACO, 1701 Columbia 

Avenue, College Park, Georgia 30337; 

telephone: (404) 474–5587; fax: (404) 474– 

5606; email: hector.hernandez@faa.gov. 

(2) For service information identified in 

this AD, contact Piper Aircraft, Inc., 2926 

Piper Drive, Vero Beach, Florida 32960; 

telephone: (772) 567–4361; Internet: 

www.piper.com. You may review copies of 

the service information at the FAA, Small 

Airplane Directorate, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the FAA, call 

(816) 329–4148. 

Issued in Kansas City, Missouri, on July 25, 

2012. 

James Jackson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–18618 Filed 8–1–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0726; Directorate 

Identifier 2012–NM–023–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 

series airplanes. This proposed AD was 

prompted by cases of on-ground failure 

of the screw cap or end cap of hydraulic 

accumulators on other airplane models, 

resulting in high-energy impact damage 

to adjacent systems and structure. This 

proposed AD would require inspecting 

for a part number and replacing the 

affected parking brake hydraulic 

accumulator, and relocating the parking 

brake accumulator, on the subject 

airplanes. We are proposing this AD to 

prevent failure of the screw caps and/or 

end caps of the parking brake hydraulic 

accumulator, which could result in 

damage to the airplane’s primary 

structures, with potential adverse effect 

on the airplane’s controllability. 

DATES: We must receive comments on 

this proposed AD by September 17, 

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: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7318; 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–2012–0726; Directorate Identifier 

2012–NM–023–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–2012–04, 

dated January 13, 2012 (referred to after 

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

condition for the specified products. 

The MCAI states: 

Seven cases of on-ground hydraulic 

accumulator/screw cap/end cap failure have 

been experienced on CL–600–2B19 (CRJ) 

aeroplanes, resulting in loss of the associated 

hydraulic system and high-energy impact 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS