57534 Federal Register / Vol. 77, No. 181 / Tuesday, September 18, 2012 / Proposed Rules 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0983; Directorate 

Identifier 2012–CE–001–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 supersede an 

existing airworthiness directive (AD) 

that applies to all Piper Aircraft, Inc. 

Models PA–31, PA–31–325, and PA– 

31–350 airplanes. The existing AD 

currently requires a detailed repetitive 

inspection of the exhaust system 

downstream of the turbochargers and 

repair or replacement of parts as 

necessary. Since we issued that AD, 

forced landings of aircraft have occurred 

due to exhaust system failures upstream 

of aircraft turbochargers and between 

recurring detailed inspections. This 

proposed AD would require both visual 

and detailed repetitive inspections, 

expanding the inspection scope to 

include the entirety of each airplane 

exhaust system. We are proposing this 

AD to prevent the possibility of an 

inflight powerplant fire due to an 

exhaust system failure. 

DATES: We must receive comments on 

this proposed AD by November 2, 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; fax: (772) 978–6573; Internet: 

www.piper.com/home/pages/ 

Publications.cfm. 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: Gary 

Wechsler, Aerospace Engineer, Atlanta 

Aircraft Certification Office, FAA, 1701 

Columbia Avenue, College Park, Georgia 

30337; telephone: (404) 474–5575; fax: 

(404) 474–5606; email: 

gary.wechsler@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–2012–0983; Directorate Identifier 

2012–CE–001–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 April 7, 1986, AD 82–16–05 R1, 

amendment 39–5278 (51 FR 11707–01, 

April 7, 1986), was published in the 

Federal Register for certain Piper 

Aircraft, Inc. Models PA–31, PA–31– 

325, and PA–31–350 airplanes. That AD 

requires a detailed repetitive inspection 

of the exhaust system downstream of 

the turbochargers and repair or 

replacement of parts as necessary. That 

AD resulted from exhaust system 

failures downstream from turbochargers. 

We issued that AD to prevent the 

possibility of an inflight powerplant fire 

due to an exhaust system failure. 

Actions Since Existing AD Was Issued 

Since we issued AD 82–16–05 R1 (51 

FR 11707–01, April 7, 1986), forced 

landings of aircraft have occurred due to 

exhaust system failures upstream of 

aircraft turbochargers and between 

recurring detailed inspections. 

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 these same 

type designs. 

Proposed AD Requirements 

This proposed AD would retain 

certain requirements of AD 82–16–05 R1 

(51 FR 11707–01, April 7, 1986). This 

proposed AD would require a detailed 

repetitive inspection of the entire 

exhaust systems. 

Costs of Compliance 

We estimate that this proposed AD 

affects 1,016 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Visual inspection ............... 2 work-hours × $85 per hour = $170 ........................ Not applicable .................. $170 $172,720 

Disassembled inspection .. 5 work-hours × $85 per hour = $425 ........................ Not applicable .................. 425 431,800 

The on-condition costs of exhaust 

system part repairs and replacement 

cannot be predicted because the 

multitude of manner and environments 

in which aircraft operate will result in 

widely varying exhaust system 

conditions over time. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 77, No. 181 / Tuesday, September 18, 2012 / Proposed Rules 57535 

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) 

82–16–05 R1, Amendment 39–5278 (51 

FR 11707–01, April 7, 1986), and adding 

the following new AD: 

Piper Aircraft, Inc.: Docket No. FAA– 

2012–0983; Directorate Identifier 2012–CE– 

001–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by November 2, 2012. 

(b) Affected ADs 

This AD supersedes AD 82–16–05 R1, 

Amendment 39–5278. 

(c) Applicability 

This AD applies to turbocharged Piper 

Aircraft, Inc. Models PA–31, PA–31–325, and 

PA–31–350 airplanes, all serial numbers, 

certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 78, Engine Exhaust. 

(e) Unsafe Condition 

This AD was prompted by the forced 

landings of aircraft due to exhaust system 

failures between recurring detailed 

inspections. We are issuing this AD to 

prevent the possibility of an inflight 

powerplant fire due to an exhaust system 

failure. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Visual Inspection 

Within the next 50 hours time-in-service 

(TIS) after the effective date of this AD or 

within the next 6 months after the effective 

date of this AD, whichever occurs first, and 

repetitively thereafter at intervals not to 

exceed 50 hours TIS or 6 months, whichever 

occurs first, inspect the entirety of each 

exhaust system by gaining access to (but not 

disassembling) each exhaust system. Using a 

flashlight and a mirror, visually inspect the 

entirety of each exhaust system for bulges, 

burned areas, corrosion, cracks, deformation, 

exhaust stains, and holes and pinholes. 

Riveted couplings should be checked for 

loose rivets and cracks emanating from rivet 

holes. Inspection procedure references can be 

found in FAA Advisory Circular 43.13–1B, 

Change 1, dated September 27, 2001, 

Acceptable Methods, Techniques, And 

Practices—Aircraft Inspection and Repair 

(http://www.airweb.faa.gov/Regulatory_

and_Guidance_Library/rgAdvisory

Circular.nsf/0/

99C827DB9BAAC81B86256B4500596C4E

?OpenDocument&Highlight=ac%2043.13– 

1b). 

(h) Detailed Inspection 

Within the next 100 hours TIS after the 

effective date of this AD or within the next 

12 months after the effective date of this AD, 

whichever occurs first, and repetitively 

thereafter at intervals not to exceed 100 hours 

TIS or 12 months, whichever occurs first, do 

the following: 

(1) Gain access to each exhaust system and 

remove all exhaust system v-band couplings. 

Note 1 to paragraph (h) of this AD: During 

removal, we recommend not opening the vband couplings more than the MINIMUM 

diameter necessary to clear coupled flanges. 

(2) Using either a dye-penetrant inspection 

method or a light and a 10-power magnifying 

glass (inspection procedure references can be 

found in FAA Advisory Circular 43.13–1B, 

Change 1, dated September 27, 2001, 

Acceptable Methods, Techniques, and 

Practices–Aircraft Inspection and Repair 

(http://www.airweb.faa.gov/Regulatory_and

_Guidance_Library/rgAdvisoryCircular.nsf/0/

99C827DB9BAAC81B86256B4500596C4E?

OpenDocument&Highlight=ac%2043.13–1b), 

accomplish the following: 

(i) Inspect the tailpipe assembly for damage 

including bulges, burned areas, corrosion, 

cracks, deformation, exhaust stains, and 

holes and pinholes. 

(ii) Inspect each v-band coupling for 

damage including bending, cracks (those 

emanating from rivets, too), failed spot 

welds, indications of exhaust flanges 

bottoming in couplings, loose rivets, 

overstress, and spreading of v-band segments. 

Inspect the bolt and nut of each coupling for 

thread damage. 

(iii) Inspect the flanges of the exhaust 

system (which mate with the transition), the 

transition, the tail pipe, and the turbocharger 

(uncoupled) for cracks, distortion, and 

evidence indicative of improper surface 

mating. 

(3) Inspect the three exhaust system slip 

joints between each turbocharger and its 

closest riser for seizure. 

Note 2 to paragraph (h) of this AD: We 

established the repetitive inspection 

compliance times of this AD so they may 

coincide with scheduled oil changes and 

annual inspections. 

(i) Corrective Actions 

(1) If any damage is found as a result of the 

inspections required in paragraph (g) of this 

AD, before further flight, do the following 

corrective actions: 

(i) Replace loose or damaged v-band 

couplings following the instructions in 

paragraph (k) of this AD. 

(ii) Repair or replace loose fasteners and 

damaged exhaust system parts with 

airworthy parts. 

(2) If any damage is found as a result of the 

inspections listed in paragraph (h) of this AD, 

before further flight, do the following 

corrective actions: 

(i) Replace any loose or damaged v-band 

couplings following the instructions in 

paragraph (k) of this AD. 

(ii) Repair or replace loose fasteners, seized 

slip joints, and damaged exhaust system 

parts with airworthy parts. 

(iii) Replace any part exhibiting flange 

cracking or distortion, and remove any 

carbon deposits from mating flange surfaces. 

(j) Mandatory Replacement 

(1) Initially replace the v-band coupling 

following the procedures in paragraph (k) of 

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57536 Federal Register / Vol. 77, No. 181 / Tuesday, September 18, 2012 / Proposed Rules 

this AD at whichever of the following occurs 

later: 

(i) The v-band coupling reaches a total of 

1,000 hours time-in-service (TIS); or 

(ii) 50 hours TIS after the effective date of 

this AD, or 6 months after the effective date 

of this AD, whichever occurs earlier. 

(2) After the initial replacement required in 

paragraph (j)(1) of this AD, repetitively 

thereafter replace the v-band coupling every 

1,000 hours TIS. 

(k) Flange and V-Band Coupling 

(1) Install serviceable and replacement vband couplings following the applicable 

instructions contained in Piper Aircraft 

Corporation Service Bulletin No. 644E, dated 

May 9, 2012 and/or Lycoming Service 

Instruction No. 1238B, dated January 6, 2010. 

(2) Use the applicable torque values 

specified within Piper Aircraft Corporation 

Service Bulletin No. 644E, dated May 9, 

2012, for Piper v-band couplings; and within 

Lycoming Service Instruction No. 1238B, 

dated January 6, 2010, for Lycoming v-band 

couplings; making sure the torque indicator 

wrench socket is properly aligned to prevent 

side loads upon the (v-band coupling) bolt. 

(3) Align each flange couple so that mating 

flange surfaces are flat against each other (do 

not use a v-band coupling to pull flanges into 

alignment). 

(4) Verify that the locknuts exhibit a 

prevailing torque, and replace any locknuts 

and/or mating couplings with airworthy parts 

when locknuts are not exhibiting a prevailing 

torque. 

Note 1 to paragraph (k) of this AD: During 

installation, we recommend not opening the 

v-band coupling more than the MINIMUM 

diameter necessary to clear coupled flanges. 

(l) 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. 

(m) Related Information 

(1) For more information about this AD, 

contact Gary Wechsler, Aerospace Engineer, 

Atlanta ACO, FAA, 1701 Columbia Avenue, 

College Park, Georgia 30337; telephone: (404) 

474–5575; fax: (404) 474–5606; email: 

gary.wechsler@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; fax: (772) 978– 

6573; Internet: www.piper.com/home/pages/ 

Publications.cfm. 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. 

Issued in Kansas City, Missouri, on 

September 11, 2012. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–22953 Filed 9–17–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0936; Directorate 

Identifier 2011–NM–269–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company 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 

The Boeing Company Model 737–700 

and –700C series airplanes. This 

proposed AD was prompted by reports 

of early fatigue cracks at chem-mill 

areas on the crown skin panels. This 

proposed AD would require repetitive 

inspections for cracking of the fuselage 

skin at certain locations at chem-mill 

areas, and repair if necessary. We are 

proposing this AD to detect and correct 

fatigue cracking of the skin panel at the 

specified chem-mill step locations, 

which could result in rapid 

decompression of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 2, 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 Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https:// 

www.myboeingfleet.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 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: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6447; fax: (425) 917–6590; email: 

Wayne.Lockett@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– 

2012–0936; Directorate Identifier 2011– 

NM–269–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 early fatigue 

cracks near chem-mill areas on the 

crown skin panels of Model 737–300, 

–400, and –500 series airplanes. The 

cracks resulted from high stresses in the 

areas where chem-mill pockets are 

adjacent to non-chem-mill areas. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS