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

76066 

Vol. 76, No. 234 

Tuesday, December 6, 2011 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1259; Directorate 

Identifier 2011–NM–181–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 777 

airplanes. This proposed AD was 

prompted by reports of corrosion 

damage on the outer diameter chrome 

surface of the horizontal stabilizer pivot 

pins. Micro cracks in the chrome plating 

of the pivot pin, some of which 

extended into the base metal, were also 

reported. This condition, if not 

corrected, could result in a fractured 

horizontal stabilizer pivot pin, which 

may cause excessive horizontal 

stabilizer freeplay and structural 

damage significant enough to result in 

loss of control of the airplane. This 

proposed AD would require replacing 

the existing horizontal stabilizer pivot 

pins with new or reworked pivot pins 

having improved corrosion resistance, 

doing repetitive inspections after 

installing the pivot pins, and doing 

corrective actions if necessary. We are 

proposing this AD to correct the unsafe 

condition on these products. 

DATES: We must receive comments on 

this proposed AD by January 20, 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: 

James Sutherland, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6533; fax: (425) 917–6590; email: 

james.sutherland@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– 

2011–1259; Directorate Identifier 2011– 

NM–181–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 reports of corrosion 

damage on the outer diameter chrome 

surface of the horizontal stabilizer pivot 

pins. Micro cracks in the chrome plating 

of the pivot pin, some of which 

extended into the base metal, were also 

reported. This condition, if not 

corrected, could result in a fractured 

horizontal stabilizer pivot pin, which 

may cause excessive horizontal 

stabilizer freeplay and structural 

damage significant enough to result in 

loss of control of the airplane. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 777–55A0018, dated July 27, 

2011. The service information describes 

procedures for replacing the inner and 

outer pivot pins of the horizontal 

stabilizer with new or reworked pivot 

pins, including replacing the spacer 

with a new spacer or with one that has 

been determined to be without 

corrosion damage or other irregularities. 

That service bulletin describes 

procedures for doing repetitive detailed 

inspections for cracks, corrosion 

damage, or other irregularities of the 

outer and inner pivot pins after their 

replacement, and doing corrective 

actions if necessary. That service 

bulletin also describes procedures for 

doing repetitive ultrasonic inspections 

for cracks of the outer pivot pins after 

their replacement, and doing corrective 

actions if necessary. Corrective actions 

include replacing any pivot pin having 

cracking, corrosion damage, or other 

irregularities, with a new or serviceable 

pivot pin. 

The compliance time for replacing the 

inner and outer pivot pins is the later of: 

(1) Before the accumulation of 16,000 

total flight cycles, or within 3,000 days 

after the issuance of the original 

certificate of airworthiness or the 

original export certificate (whichever 

occurs first); and (2) within 750 days 


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Federal Register / Vol. 76, No. 234 / Tuesday, December 6, 2011 / Proposed Rules 76067 

‘‘after the original issue date of this 

service bulletin.’’ The first postreplacement inspection is within 32,000 

flight cycles or 6,000 days (whichever 

occurs first after the pin replacement). 

The repetitive inspection interval is 

16,000 flight cycles or 3,000 days 

(whichever occurs first); or 12,000 flight 

cycles or 3,000 days (whichever occurs 

first); depending on airplane group. 

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. 

Costs of Compliance 

We estimate that this proposed AD 

affects 155 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 

Replacement of horizontal 

stabilizer pivot pins.

16 work-hours × $85 per hour 

= $1,360.

$11,452 $12,812 .................................. $1,985,860. 

Repetitive inspections ............ 22 work-hours × $85 per hour 

= $1,870 per inspection 

cycle.

0 $1,870 per inspection cycle ... $289,850 per inspection 

cycle. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspections. 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 

Pivot pin or spacer replacement ............................. 16 work-hours × $85 per hour = $1,360 ................ $11,452 $12,812 

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– 

2011–1259; Directorate Identifier 2011– 

NM–181–AD. 

(a) Comments Due Date 

We must receive comments by January 20, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200, –200LR, –300, –300ER, and 

777F series airplanes, certificated in any 

category; as identified in Boeing Alert 

Service Bulletin 777–55A0018, dated July 27, 

2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 55, Stabilizers. 

(e) Unsafe Condition 

This AD was prompted by reports of 

corrosion damage on the outer diameter 

chrome surface of the horizontal stabilizer 

pivot pins. Micro cracks in the chrome 

plating of the pivot pin, some of which 

extended into the base metal, were also 

reported. This condition, if not corrected, 

could result in a fractured horizontal 

stabilizer pivot pin, which may cause 

excessive horizontal stabilizer freeplay and 


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76068 Federal Register / Vol. 76, No. 234 / Tuesday, December 6, 2011 / Proposed Rules 

structural damage significant enough to 

result in loss of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Pivot Pin Replacement 

At the applicable time specified in 

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

Alert Service Bulletin 777–55A0018, dated 

July 27, 2011, except as required by 

paragraph (i)(2) of this AD, replace the pivot 

pins of the horizontal stabilizer with new or 

reworked pivot pins, including replacing the 

spacer with a new spacer or with one that has 

been determined to be without corrosion 

damage or other irregularities; in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 777–55A0018, 

dated July 27, 2011. 

(h) Repetitive Inspections 

At the applicable time specified in 

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

Alert Service Bulletin 777–55A0018, dated 

July 27, 2011: Do detailed inspections for 

cracks, corrosion damage, or other 

irregularity of the outer and inner pivot pins; 

and an ultrasonic inspection for cracking of 

the outer pivot pins; and do all applicable 

corrective actions; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–55A0018, dated July 27, 

2011. Corrective actions must be done before 

further flight. Repeat the inspections at the 

applicable interval specified in paragraph 

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

Bulletin 777–55A0018, dated July 27, 2011, 

except as provided by paragraph (i)(1) of this 

AD. 

Note 1: The Accomplishment Instructions 

of Boeing Alert Service Bulletin 777– 

55A0018, dated July 27, 2011, 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 design approval holder 

document must be used to comply with the 

AD. 

(i) Exceptions 

The following exceptions to Boeing Alert 

Service Bulletin 777–55A0018, dated July 27, 

2011, apply to this AD. 

(1) Where the Repeat Interval column of 

tables 2 and 3 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 777–55A0018, dated July 27, 2011, 

specify a compliance time, this AD requires 

compliance within the specified compliance 

time after the most recent inspection. 

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

Boeing Alert Service Bulletin 777–55A0018, 

dated July 27, 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.’’ 

(j) 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. 

(k) Related Information 

(1) For more information about this AD, 

contact James Sutherland, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, Washington 

98057–3356; phone: (425) 917–6533; fax: 

(425) 917–6590; email: 

james.sutherland@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 

November 23, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–31312 Filed 12–5–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1285; Directorate 

Identifier 2010–SW–073–AD] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for 

Eurocopter Deutschland GmbH Model 

BO–105A, BO–105C, BO–105LS A–1, 

BO–105LS A–3, and BO–105S 

helicopters. This proposed AD would 

require inspecting certain main rotor 

blades for debonding of the erosion 

protective shell. If the erosion protective 

shell is debonded, you would be 

required to replace the main rotor blade 

with an airworthy main rotor blade. 

This proposed AD is prompted by the 

results of an inspection on a BO–105 

helicopter where debonding was 

discovered on a main rotor blade 

erosion protective shell, and it was 

determined that the debonding was due 

to incorrect installation of the erosion 

protective shell. Subsequently, an 

incident occurred where a BO–105 

helicopter lost its main rotor blade 

erosion protective shell during flight. 

The actions specified by this proposed 

AD are intended to detect debonding of 

the main rotor blade erosion protective 

shell which could lead to an unbalanced 

main rotor, high vibrations, damage to 

the tail boom or tail rotor, and loss of 

control of the helicopter. 

DATES: Comments must be received on 

or before February 6, 2012. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD: 

• 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. 


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