Federal Register / Vol. 77, No. 14 / Monday, January 23, 2012 / Proposed Rules 3187 

That airspace extending upward from 700 

feet above the surface within a 6-mile radius 

of Queen Anne E.R. Heliport. 

Issued in College Park, Georgia, on January 

12, 2012. 

Michael Vermuth, 

Acting Manager, Operation Support Group, 

Eastern Service Center, Air Traffic 

Organization. 

[FR Doc. 2012–1203 Filed 1–20–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0035; Directorate 

Identifier 2011–NM–178–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 

Model 767–200 and –300 series 

airplanes. This proposed AD was 

prompted by reports of fatigue cracking 

on the lower main sill inner chord of the 

hatch opening of the overwing 

emergency exit. This proposed AD 

would require repetitive inspections for 

cracking, corrosion damage, and any 

other irregularity of the lower main sill 

inner chord and surrounding structure, 

and repair if necessary. We are 

proposing this AD to detect and correct 

fatigue cracking on the lower main sill 

inner chord of the hatch opening of the 

overwing emergency exit, which could 

result in reduced structural integrity of 

the hatch opening of the overwing 

emergency exit and consequent rapid 

decompression of the airplane. 

DATES: We must receive comments on 

this proposed AD by March 8, 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, 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 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: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6577; fax: (425) 917–6590; e-mail: 

berhane.alazar@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– 

2012–0035; Directorate Identifier 2011– 

NM–178–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 fatigue 

cracking on the lower main sill inner 

chord of the hatch opening of the 

overwing emergency exit on an airplane 

that had completed 42,079 total flight 

cycles. This condition, if not corrected, 

could result in reduced structural 

integrity of the hatch opening of the 

overwing emergency exit and 

consequent rapid decompression of the 

airplane. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 767–53A0228, dated July 28, 

2011. This service information describes 

procedures, depending on the airplane 

configuration, for repetitive high 

frequency eddy current inspections for 

cracking of the lower main sill inner 

chord around body station (STA) 883.5; 

repetitive detailed inspections for 

cracking, corrosion damage, and any 

other irregularity of the lower main sill 

inner chord and surrounding structure 

around STA 883.5; and repetitive 

detailed inspections for cracking, 

corrosion damage, and any other 

irregularity of the lower main sill inner 

chord and surrounding structure around 

STA 903.5. This service information 

also describes procedures for repair of 

certain cracking, corrosion damage, or 

other irregularity, if necessary. 

The initial compliance time for the 

inspections is at the later of: (1) before 

37,500 total flight cycles and (2) within 

3,000 flight cycles ‘‘after the original 

issue date of the service bulletin.’’ The 

repetitive intervals are 3,750 flight 

cycles and 7,500 flight cycles, 

depending on the inspection type. 

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 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between the Proposed AD 

and the Service Information.’’ 

Differences Between Proposed AD and 

the Service Information 

Boeing Alert Service Bulletin 767– 

53A0228, dated July 28, 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: 


srobinson on DSK4SPTVN1PROD with PROPOSALS
3188 Federal Register / Vol. 77, No. 14 / Monday, January 23, 2012 / Proposed Rules 

• 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 767– 

53A0228, dated July 28, 2011, specifies 

that the sequence of steps to do the 

required actions can be changed, but 

this proposed AD requires that the 

actions must be done in sequence. 

Costs of Compliance 

We estimate that this proposed AD 

affects 377 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 

Inspection ........ 28 work-hours × $85 per hour = 

$2,380 per inspection cycle.

$0 $2,380 per inspection cycle .............. $897,260 per inspection cycle. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this proposed 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 

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): 

The Boeing Company: Docket No. FAA– 

2012–0035; Directorate Identifier 2011– 

NM–178–AD. 

(a) Comments Due Date 

We must receive comments by March 8, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 767–200 and –300 series airplanes, 

certificated in any category, as specified in 

Boeing Alert Service Bulletin 767–53A0228, 

dated July 28, 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 

fatigue cracking on the lower main sill inner 

chord of the hatch opening of the overwing 

emergency exit. We are issuing this AD to 

detect and correct fatigue cracking on the 

lower main sill inner chord of the hatch 

opening of the overwing emergency exit, 

which could result in reduced structural 

integrity of the hatch opening of the 

overwing emergency exit and consequent 

rapid decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections and Repair 

Within the applicable compliance time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 767–53A0228, 

dated July 28, 2011, except as provided by 

paragraph (h)(3) of this AD: Do a high 

frequency eddy current (HFEC) inspection for 

cracking of the lower main sill inner chord 

around body station (STA) 883.5; a detailed 

inspection for cracking, corrosion damage, 

and any other irregularity, of the lower main 

sill inner chord and surrounding structure 

around STA 883.5; and a detailed inspection 

for cracking, corrosion damage, or other 

irregularity, of the lower main sill inner 

chord and surrounding structure around STA 

903.5; as applicable; and do all applicable 

repairs; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–53A0228, dated July 28, 

2011, except as required by paragraphs (h)(1) 

and (h)(2) of this AD. Do all applicable 

repairs before further flight. Repeat the 

applicable inspections thereafter within the 

applicable times and intervals specified in 

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

Alert Service Bulletin 767–53A0228, dated 

July 28, 2011. Doing a structural repair in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–53A0228, dated July 28, 2011, 

terminates the repetitive inspections for that 

location only. 

(h) Exceptions 

(1) If any cracking, corrosion damage, or 

other irregularity is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 767–53A0228, dated 

July 28, 2011, specifies to contact Boeing for 

appropriate action: Before further flight, 

repair the cracking, corrosion damage, or 

other irregularity, using a method approved 

in accordance with the procedures specified 

in paragraph (i) of this AD. 


srobinson on DSK4SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 14 / Monday, January 23, 2012 / Proposed Rules 3189 

(2) Where Boeing Alert Service Bulletin 

767–53A0228, dated July 28, 2011, specifies 

that the sequence of steps to do the actions 

can be changed, this AD does not allow the 

sequence of steps to be changed. 

(3) Where Boeing Alert Service Bulletin 

767–53A0228, dated July 28, 2011, specifies 

a compliance time ‘‘after the original issue 

date of this service bulletin,’’ this AD 

requires compliance within the specified 

compliance time ‘‘after the effective date of 

this AD.’’ 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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. 

Information may be e-mailed 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 the 

Boeing Commercial Airplanes Organization 

Designation Authorization (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 14 CFR 

25.571, Amendment 45, and the approval 

must specifically refer to this AD. 

(j) Related Information 

(1) For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: (425) 917–6577; fax: (425) 917– 

6590; e-mail: berhane.alazar@faa.gov. 

(2) 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. 

Issued in Renton, Washington on January 

13, 2012. 

John Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–1202 Filed 1–20–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0036; Directorate 

Identifier 2011–NM–142–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 test reports showing that 

failure of a retract port flexible hose of 

a main landing gear (MLG) retraction 

actuator could cause excessive 

hydraulic fluid leakage. This proposed 

AD would require a detailed inspection 

for defects and damage of the retract 

port flexible hose on the left and right 

MLG retraction actuator, and 

replacement of the flexible hose if 

needed. We are proposing this AD to 

detect and correct defects and damage of 

the retract port flexible hose which 

could lead to an undamped extension of 

the MLG and could result in MLG 

structural failure, leading to an unsafe 

asymmetric landing configuration. 

DATES: We must receive comments on 

this proposed AD by March 8, 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–2012–0036; Directorate Identifier 

2011–NM–142–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–2011–14, 

dated June 17, 2011 (referred to after 

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

condition for the specified products. 

The MCAI states: 

Testing has shown that in the event of a 

main landing gear (MLG) retraction actuator 

retract port flexible hose failure, in-flight 

vibrations may cause excessive hydraulic 

fluid leakage. This could potentially lead to 

an undamped extension of the MLG, which 


srobinson on DSK4SPTVN1PROD with PROPOSALS