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

78574 

Vol. 76, No. 243 

Monday, December 19, 2011 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1322; Directorate 

Identifier 2011–NM–211–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 all The 

Boeing Company Model 767 airplanes. 

This proposed AD was prompted by 

reports of cracks of the underwing 

longeron fittings in the wing center 

section which could result in loss of the 

primary load path between the fuselage 

and the wing box, and consequent 

catastrophic damage to the wing box 

and failure of the wing. This proposed 

AD would require repetitive high 

frequency eddy current (HFEC) 

inspections of the underwing longeron 

fitting for cracking, and related 

investigative and corrective actions if 

necessary. We are proposing this AD to 

detect and correct the unsafe condition 

on these products. 

DATES: We must receive comments on 

this proposed AD by February 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 AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H– 

65, Seattle, Washington 98124–2207; 

phone: (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 

(ACO), 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6577; fax: (425) 917–6590; email: 

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– 

2011–1322; Directorate Identifier 2011– 

NM–211–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 have received three reports of 

cracks of the underwing longeron 

fittings in the wing center section. One 

operator reported finding cracks in the 

underwing longeron fittings of the left 

and right wing center section. The 

cracks found were in the same location 

on both fittings and appeared to run 

through the entire thickness of the 

forward edge of the fitting at the radius 

corner of the vertical/horizontal flange. 

The lengths of cracks were 

approximately 0.300 to 0.375 inch long. 

The airplane had accumulated 37,000 

total flight cycles. Similar cracks were 

found on a fatigue test airplane at these 

locations. Boeing estimates that it would 

take 25,000 flight cycles for the cracks 

to grow from 0.375 inch to 1.8 inches. 

Another operator reported finding a 

crack in the underwing longeron fitting 

of the left wing center section during 

normal maintenance. The crack was 

approximately one inch long and started 

from the radius of the fitting flange. The 

airplane had accumulated 16,655 total 

flight cycles. 

Such cracking, if not detected and 

corrected, could result in loss of the 

primary load path between the fuselage 

and the wing box, and consequent 

catastrophic damage to the wing box 

and failure of the wing. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 767–57A0126, dated August 12, 

2011. This service information describes 

procedures for repetitive HFEC 

inspections to detect cracking of the 

underwing longeron fitting, and related 

investigative and corrective actions if 

necessary. The related investigative 

action is an HFEC inspection to detect 

cracking of the tension bolt hole and the 

front spar lower chord. The corrective 

actions include replacing the underwing 

longeron fitting, and contacting The 

Boeing Company for repair instructions 

and doing the repair. 

The compliance times are dependent 

on the total number of flight hours and 

flight cycles accumulated on the 

airplane. For certain airplanes, the 

initial compliance time is within 3,000 

flight cycles or 7,000 flight hours 


emcdonald on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 76, No. 243 / Monday, December 19, 2011 / Proposed Rules 78575 

(whichever is first) after the date of the 

service bulletin. For other airplanes, the 

initial compliance time is the later of: 

(1) Before 16,000 total flight cycles or 

35,000 total flight hours (whichever is 

first), and (2) within 6,000 flight cycles 

or 14,000 flight hours (whichever is 

first) after the date of the service 

bulletin. 

The repetitive inspection interval is 

12,000 flight cycles or 28,000 flight 

hours (whichever is first). The first 

repetitive inspection for airplanes on 

which the underwing longeron fitting is 

replaced is 16,000 flight cycles or 

35,000 flight hours (whichever is first) 

after replacement. 

We have also reviewed Boeing Service 

Bulletin 767–57A0126, Revision 1, 

dated November 9, 2011 (short form 

revision), which changes the part 

number of a certain washer. 

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 the Proposed AD 

and the Service Information 

Boeing Alert Service Bulletin 767– 

57A0126, dated August 12, 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. 

Interim Action 

We consider this proposed AD 

interim action. The design approval 

holder is currently developing a 

modification that will address the 

unsafe condition identified in this AD. 

Once this modification is developed, 

approved, and available, we might 

consider additional rulemaking. 

Costs of Compliance 

We estimate that this proposed AD 

affects 417 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 

Repetitive HFEC inspection.3 work-hours × $85 per hour = $255 per inspection cycle.$0 $255 per inspection 

cycle.

$106,335 per inspection 

cycle. 

We estimate the following costs to do 

any necessary inspections and 

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 on-condition actions. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Tension bolt hole and the front spar lower 

chord HFEC inspection and fitting replacement.

104 work-hours × $85 per hour = $8,840 ....... Up to $11,551 ............ Up to $20,391. 

We have received no definitive data 

that would enable us to provide cost 

estimates for cracking repairs 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. 


emcdonald on DSK5VPTVN1PROD with PROPOSALS
78576 Federal Register / Vol. 76, No. 243 / Monday, December 19, 2011 / Proposed Rules 

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– 

2011–1322; Directorate Identifier 2011– 

NM–211–AD. 

(a) Comments Due Date 

We must receive comments by February 2, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 767–200, –300, –300F, and 

–400ER series airplanes; certificated in any 

category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

of the underwing longeron fittings in the 

wing center section. We are issuing this AD 

to detect and correct such cracking, which 

could result in loss of the primary load path 

between the fuselage and the wing box, and 

consequent catastrophic damage to the wing 

box and failure of the wing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections, Related Investigative 

Actions, and Corrective Actions 

Except as provided by paragraphs (h)(2) 

and (h)(3) of this AD, at the applicable time 

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

Boeing Alert Service Bulletin 767–57A0126, 

dated August 12, 2011: Do a high frequency 

eddy current (HFEC) inspection to detect 

cracking of the underwing longeron fitting; 

and do all applicable related investigative 

and corrective actions; in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 767–57A0126, dated 

August 12, 2011, as revised by Boeing 

Service Bulletin 767–57A0126, Revision 1, 

dated November 9, 2011 (short form 

revision), except as provided by paragraph 

(h)(1) of this AD. Do all applicable related 

investigative and corrective actions before 

further flight. Repeat the inspection of the 

underwing longeron fitting thereafter at the 

applicable time and intervals specified in 

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

Alert Service Bulletin 767–57A0126, dated 

August 12, 2011. 

(h) Exceptions to Paragraph (g) of This AD 

(1) If, during accomplishment of the related 

investigative action required by this AD, any 

cracking is found, and Boeing Alert Service 

Bulletin 767–57A0126, dated August 12, 

2011, specifies to contact Boeing for repair 

instructions: Before further flight, do the 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (i) of this AD. 

(2) Where Paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 767–57A0126, 

dated August 12, 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.’’ 

(3) The Condition column of Paragraph 

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

Bulletin 767–57A0126, dated August 12, 

2011, refers to total flight cycles and total 

flight hours ‘‘as of the original issue date of 

this service bulletin.’’ However, this AD 

applies to the airplanes with the specified 

total flight cycles or total flight hours ‘‘as of 

the effective date of this AD.’’ 

Note 1: The service bulletin 

accomplishment instructions might refer to 

other procedures. When the words ‘‘refer to’’ 

are used and the operator has an accepted 

alternative procedure, the accepted 

alternative procedure can be used to comply 

with the AD. When the words ‘‘in accordance 

with’’ are included in the instruction, the 

procedure in the service bulletin must be 

used to comply with the 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 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 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 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 (ACO), 1601 Lind 

Avenue SW., Renton, Washington 98057– 

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

6590; email: 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; phone: 

(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 

December 9, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–32387 Filed 12–16–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2011–1275; Airspace 

Docket No. 11–ANM–26] 

Proposed Amendment of Class E 

Airspace; Hugo, CO 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

amend Class E airspace at Hugo, CO. 

Decommissioning of the Hugo Tactical 

Air Navigation System (TACAN) has 

made this action necessary for the safety 

and management of Instrument Flight 

Rules (IFR) operations in the vicinity of 

the Hugo Very High Frequency OmniDirectional Radio Range/Distance 

Measuring Equipment (VOR/DME). This 

action also would make a minor 

adjustment to the geographic 

coordinates of the VOR/DME and make 

a correction to the regulatory text. 

DATES: Comments must be received on 

or before February 2, 2012. 

ADDRESSES: Send comments on this 

proposal to the U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590; telephone (202) 

366–9826. You must identify FAA 

Docket No. FAA–2011–1275; Airspace 

Docket No. 11–ANM–26, at the 

beginning of your comments. You may 


emcdonald on DSK5VPTVN1PROD with PROPOSALS