Federal Register / Vol. 76, No. 211 / Tuesday, November 1, 2011 / Rules and Regulations 67343 

Services, 65921 Tarbes Cedex 9, France; 

telephone: +33 (0)5 62 41 73 00; fax: +33 (0)5 

62 41 7654; or in the United States contact 

SOCATA North America, Inc., North Perry 

Airport, 7501 South Airport Road, Pembroke 

Pines, Florida 33023; telephone: (954) 893– 

1400; fax: (954) 964–4141; Internet: http:// 

www.socatanorthamerica.com. 

(3) 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. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call (202) 741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Kansas City, Missouri, on 

October 24, 2011. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–27949 Filed 10–31–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1162; Directorate 

Identifier 2011–NM–186–AD; Amendment 

39–16856; AD 2011–23–05] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 737–300, –400, and 

–500 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain Model 737–300, –400, and –500 

series airplanes. That AD currently 

requires repetitive inspections for 

cracking of the 1.04-inch nominal 

diameter wire penetration hole, and 

applicable related investigative and 

corrective actions. This AD reduces the 

compliance times for those actions. This 

AD was prompted by reports of cracking 

in the frame, or in the frame and frame 

reinforcement, common to the 1.04-inch 

nominal diameter wire penetration hole 

intended for wire routing; and recent 

reports of multiple adjacent frame 

cracking found before the compliance 

time required by the existing AD. Such 

cracking could reduce the structural 

capability of the frames to sustain limit 

loads, and result in cracking in the 

fuselage skin and subsequent rapid 

depressurization of the airplane. We are 

issuing this AD to correct the unsafe 

condition on these products. 

DATES: This AD is effective November 

16, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 16, 2011. 

We must receive any comments on 

this AD by December 16, 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: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; 

telephone (206) 544–5000, extension 1; 

fax (206) 766–5680; email 

me.boecom@boeing.com; 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 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, Seattle 

Aircraft Certification Office (ACO), 

FAA, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 

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

wayne.lockett@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On August 26, 2009, we issued AD 

2009–02–06 R1, Amendment 39–16015 

(74 FR 45979, September 8, 2009), for 

certain Model 737–300, –400, and –500 

series airplanes. That AD requires 

repetitive inspections for cracking of the 

1.04-inch nominal diameter wire 

penetration hole in the frame and in the 

frame reinforcement, between stringers 

S–20 and S–21, on both the left and 

right sides of the airplane, and 

applicable related investigative and 

corrective actions. That AD resulted 

from reports of cracking in the frame, or 

in the frame and frame reinforcement, 

common to the 1.04-inch nominal 

diameter wire penetration hole intended 

for wire routing. We issued that AD to 

detect and correct cracking in the 

fuselage frames and frame 

reinforcements, which could reduce the 

structural capability of the frames to 

sustain limit loads, and result in 

cracking in the fuselage skin and 

subsequent rapid depressurization of 

the airplane. 

Actions Since AD Was Issued 

Since we issued AD 2009–02–06 R1, 

Amendment 39–16015 (74 FR 45979, 

September 8, 2009), we received a 

report of four adjacent cracked frames at 

body station (BS) 500B, BS 500C, BS 

500D, and BS 520 in the forward cargo 

compartment between S–20L and S–21L 

on a Model 737–300 series airplane. The 

cracks at BS 500B and BS 500C were 

completely through the frame and failsafe chord. The BS 500B frame was also 

cracked on the right-hand side. The 

cracks were discovered when the 

airplane had accumulated 44,535 total 

flight cycles and 44,876 total flight 

hours—before the compliance time 

required by AD 2009–02–06 R1. 

Relevant Service Information 

AD 2009–02–06 R1, Amendment 39– 

16015 (74 FR 45979, September 8, 

2009), referred to Boeing Alert Service 

Bulletin 737–53A1279, dated December 

18, 2007, as the appropriate source of 

service information for the required 

actions. Boeing has since revised this 

service bulletin. We reviewed Boeing 

Alert Service Bulletin 737–53A1279, 

Revision 1, dated September 2, 2011, 

which shortens the compliance time to 

30,000 total flight cycles, with a grace 

period of 30 or 90 days, and reduces the 

repetitive interval from 14,000 to 4,500 

flight cycles. The procedures are 

unchanged from those specified in 

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67344 Federal Register / Vol. 76, No. 211 / Tuesday, November 1, 2011 / Rules and Regulations 

Boeing Alert Service Bulletin 737– 

53A1279, dated December 18, 2007. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

AD Requirements 

This AD requires accomplishing the 

actions specified in the service 

information described previously, 

except as discussed under ‘‘Differences 

Between the AD and the Service 

Information.’’ 

Differences Between the AD and the 

Service Information 

Boeing Alert Service Bulletin 737– 

53A1279, Revision 1, dated September 

2, 2011, specifies to contact the 

manufacturer for instructions on how to 

repair certain conditions, but this 

proposed AD would require repairing 

those conditions in one of the following 

ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Boeing Alert Service Bulletin 737– 

53A1279, Revision 1, dated September 

2, 2011, specifies compliance with the 

Part 4 inspection by the later of 4,500 

flight cycles or 90 days—both after the 

date on this service bulletin. In some 

cases, this compliance time might occur 

before the Part 2 inspection. This AD (in 

paragraph (h)) therefore requires the 

Part 4 inspection within 4,500 flight 

cycles after accomplishment of the most 

recent Part 2 or Part 4 inspection, with 

a grace period of 90 days. We have 

coordinated this difference with Boeing. 

For certain airplanes that have 

accumulated 40,000 or more total flight 

cycles, Boeing Alert Service Bulletin 

737–53A1279, Revision 1, dated 

September 2, 2011, specifies a 30-day 

compliance time for the Part 2 

inspection. Paragraph (k)(2) of this AD 

extends that compliance time to 90 days 

for those airplanes, if the original chem.- 

milled fuselage skins have been 

replaced with solid skins. This 

difference has been coordinated with 

Boeing. 

FAA’s Justification and 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 cracking in multiple 

adjacent fuselage frames and frame 

reinforcements reduces the structural 

capability of the frames to sustain limit 

loads, and result in cracking in the 

fuselage skin and subsequent rapid 

depressurization of the airplane. 

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 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

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 No. FAA– 

2011–1162 and directorate identifier 

2011–NM–186–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 605 

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 

Inspection .............. 16 work-hours × $85 per hour = 

$1,360 per inspection cycle.

None ........ $1,360 per inspection cycle ................ $822,800 per inspection 

cycle. 

We estimate the following costs to do 

any necessary related investigative 

actions that would be required based on 

the results of the HFEC inspections. We 

have no way of determining the number 

of aircraft that might need this 

inspection: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

On-condition inspection ....................... 2 work-hours × $85 per hour = $170 .............................................................. None ........ $170 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition repair or 

optional modification specified in this 

AD. 

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 

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Federal Register / Vol. 76, No. 211 / Tuesday, November 1, 2011 / Rules and Regulations 67345 

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, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends part 39 of the Federal 

Aviation Regulations (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) 

2009–02–06 R1, Amendment 39–16015 

(74 FR 45979, September 8, 2009), and 

adding the following new AD: 

2011–23–05 The Boeing Company: 

Amendment 39–16856; Docket No. 

FAA–2011–1162; Directorate Identifier 

2011–NM–186–AD. 

(a) Effective Date 

This AD is effective November 16, 2011. 

(b) Affected ADs 

This AD supersedes AD 2009–02–06 R1, 

Amendment 39–16015 (74 FR 45979, 

September 8, 2009). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–300, –400, –500 series airplanes, 

certificated in any category; as identified in 

Boeing Alert Service Bulletin 737–53A1279, 

Revision 1, dated September 2, 2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of four 

cracked frames at certain body stations (BS) 

in the forward cargo compartment. We are 

issuing this AD to detect and correct cracking 

in the fuselage frames and frame 

reinforcements, which could reduce the 

structural capability of the frames to sustain 

limit loads, and result in cracking in the 

fuselage skin and subsequent rapid 

depressurization of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 737–53A1279, 

Revision 1, dated September 2, 2011, except 

as required by paragraphs (k)(1), (k)(2), and 

(k)(4) of this AD: Do a high frequency eddy 

current (HFEC) surface or HFEC hole/edge 

inspection for any cracking of the 1.04-inch 

nominal diameter wire penetration hole in 

the frame and frame reinforcement between 

stringer S–20 and S–21, in accordance with 

Part 2 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1279, 

Revision 1, dated September 2, 2011. 

(h) Repetitive Inspection 

Within 4,500 flight cycles after 

accomplishment of the most recent 

inspection specified in Part 2 or Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1279, Revision 1, 

dated September 2, 2011, or within 90 days 

after the effective date of this AD, whichever 

occurs later: Do an HFEC hole/edge 

inspection for cracking of the 1.04-inch 

nominal diameter wire penetration hole in 

the frame and frame reinforcement between 

S–20 and S–21, in accordance with Part 4 of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 737–53A1279, 

Revision 1, dated September 2, 2011. Repeat 

the inspection thereafter at intervals not to 

exceed 4,500 flight cycles. 

(i) Repair 

If any cracking is found during any 

inspection required by paragraph (g) or (h) of 

this AD: Before further flight, repair the crack 

including doing all related investigative and 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1279, 

Revision 1, dated September 2, 2011, except 

as required by paragraph (k)(3) of this AD. 

All related investigative and applicable 

corrective actions must be done before 

further flight. Accomplishment of the 

requirements of this paragraph terminates the 

repetitive inspection requirements of 

paragraph (h) of this AD for the repaired 

location of that frame. 

(j) Optional Terminating Action 

Accomplishment of the preventive 

modification, including doing all related 

investigative and applicable corrective 

actions, specified in Part 5 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1279, Revision 1, 

dated September 2, 2011, except as required 

by paragraph (k)(3) of this AD, terminates the 

repetitive inspection requirements of 

paragraph (h) of this AD for the modified 

location of that frame, provided the 

modification is done before further flight 

after an inspection required by paragraph (g) 

or (h) of this AD has been done, and no 

cracking was found on that frame location 

during that inspection. 

(k) Exceptions to Service Bulletin 

Specifications 

The following exceptions apply in this AD. 

(1) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1279, 

Revision 1, dated September 2, 2011, refers 

to a compliance time ‘‘from date on Revision 

1 of this service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(2) For airplanes meeting all of the criteria 

specified in paragraphs (k)(2)(i), (k)(2)(ii), 

and (k)(2)(iii) of this AD: The compliance 

time for the initial inspection specified in 

Part 2 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1279, 

Revision 1, dated September 2, 2011, and 

required by paragraph (g) of this AD, may be 

extended to 90 days after the effective date 

of this AD. 

(i) Model 737–300 series airplanes in 

Group 1, line numbers 1001 through 2565 

inclusive; 

(ii) Airplanes that have accumulated 

40,000 or more total flight cycles as of the 

effective date of this AD; and 

(iii) Airplanes on which the modification 

specified in Boeing Service Bulletin 737–53– 

1273, dated September 20, 2006; Revision 1, 

dated December 21, 2006; Revision 2, dated 

June 4, 2007; Revision 3, dated December 7, 

2009; or Revision 4, dated July 23, 2010; has 

been done, including any configuration or 

deviation that has been approved as an 

AMOC during accomplishment of these 

service bulletins, by the Boeing Commercial 

Airplanes Organization Designation 

Authorization (ODA) that has been 

authorized by the Manager, Seattle Aircraft 

Certification Office (ACO) to make those 

findings. 

(3) Where Boeing Alert Service Bulletin 

737–53A1279, Revision 1, dated September 

2, 2011 specifies to contact Boeing for 

appropriate repair instructions: Before 

further flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (m) of this AD. 

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67346 Federal Register / Vol. 76, No. 211 / Tuesday, November 1, 2011 / Rules and Regulations 

(4) The ‘‘Condition’’ column of paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1279, Revision 1, dated 

September 2, 2011, refers to total flight 

cycles, ‘‘at the date of/on this service 

bulletin.’’ However, this AD applies to the 

airplanes with the specified total flight cycles 

as of the effective date of this AD. 

(l) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

Actions done in accordance with Boeing 

Alert Service Bulletin 737–53A1279, dated 

December 18, 2007, before the effective date 

of this AD are acceptable for compliance with 

the corresponding actions required by 

paragraphs (g), (h), (i), and (j) of this AD. 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(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) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by 

Boeing Commercial Airplanes ODA that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for paragraphs (h) 

and (i) of AD 2009–02–06 R1, Amendment 

39–16015 (74 FR 45979, September 8, 2009), 

are approved as AMOCs for the 

corresponding provisions of paragraphs (g), 

(h), and (i) of this AD. 

(n) Related Information 

For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, Seattle ACO, 

FAA, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 917– 

6447; fax: (425) 917–6590; email: 

wayne.lockett@faa.gov. 

(o) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 5 

U.S.C. 552(a) and 1 CFR part 51 of the 

following service information on the date 

specified: 

(i) Boeing Alert Service Bulletin 737– 

53A1279, Revision 1, dated September 2, 

2011, approved for IBR November 16, 2011. 

(2) If you accomplish the optional actions 

specified by this AD, you must use the 

following service information to perform 

those actions, unless the AD specifies 

otherwise. The Director of the Federal 

Register approved the incorporation by 

reference (IBR) of the following service 

information on the date specified: 

(i) Boeing Alert Service Bulletin 737– 

53A1279, Revision 1, dated September 2, 

2011, approved for IBR November 16, 2011. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

(206) 544–5000, extension 1; fax (206) 766– 

5680; e-mail me.boecom@boeing.com; 

Internet 

https://www.myboeingfleet.com. 

(4) You may review copies of the service 

information at the FAA, 1601 Lind Avenue 

SW., Renton, Washington. For information 

on the availability of this material at the 

FAA, call (425) 227–1221. 

(5) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call (202) 741– 

6030, or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on October 

20, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–28053 Filed 10–31–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1161; Directorate 

Identifier 2011–CE–036–AD; Amendment 

39–16850; AD 2011–21–51] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Cessna Aircraft Company (Cessna) 

Model 525C airplanes. This emergency 

AD was sent previously to all known 

U.S. owners and operators of these 

airplanes. This AD requires replacing 

certain lithium-ion batteries installed as 

the main aircraft battery with either a 

Ni-Cad or a lead acid battery. This AD 

was prompted by a report of a battery 

fire that resulted after an energized 

ground power unit was connected to 

one of the affected airplanes equipped 

with a lithium-ion battery as the main 

aircraft battery. We are issuing this AD 

to correct the unsafe condition on these 

products. 

DATES: This AD is effective November 1, 

2011 to all persons except those persons 

to whom it was made immediately 

effective by Emergency AD 2011–21–51, 

issued on October 6, 2011, which 

contained the requirements of this 

amendment. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication identified in the 

AD as of November 1, 2011. 

We must receive comments on this 

AD by December 16, 2011. 

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 AD, contact Cessna Aircraft 

Company, Product Support, P.O. Box 

7706, Wichita, KS 67277; telephone: 

(316) 517–6000; fax: (316) 517–8500; 

email: 

Customercare@cessna.textron.com; 

Internet: http://www.cessna.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 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: 

Richard Rejniak, Aerospace Engineer, 

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