Federal Register / Vol. 77, No. 154 / Thursday, August 9, 2012 / Proposed Rules 47563 

and including Interstate Highway I–10, 

whichever is further north. 

* * * * * 

Janet Napolitano, 

Secretary. 

[FR Doc. 2012–19458 Filed 8–8–12; 8:45 am] 

BILLING CODE 9111–14–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22523; Directorate 

Identifier 2005–NM–058–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for certain The Boeing Company Model 

767 airplanes. That NPRM proposed to 

require drilling a drain hole in the 

flanged tubes for certain elevator control 

cable aft pressure seals; doing repetitive 

inspections for dirt, loose particles, or 

blockage of the flanged tube and drain 

hole for the pressure seals, and 

corrective action if necessary; replacing 

the aft air-intake duct assembly with a 

new or modified assembly and 

installing a dripshield; and installing 

gutters on the horizontal stabilizer 

center section and modifying the side 

brace fittings. That NPRM was 

prompted by reports of stiff operation of 

the elevator pitch control system and 

jammed elevator controls. This action 

revises that NPRM by proposing to 

require replacement of pressure seal 

assemblies, rather than the proposed 

drilling of drain holes; revising a certain 

compliance time and inspection type; 

adding certain optional actions; and 

revising the applicability. We are 

proposing this supplemental NPRM to 

prevent moisture from collecting and 

freezing on the elevator control system 

components, which could limit the 

ability of the flightcrew to make elevator 

control inputs and result in reduced 

controllability of the airplane. Since 

these actions impose an additional 

burden over that proposed in the 

previous NPRM, we are reopening the 

comment period to allow the public the 

chance to comment on these proposed 

changes. 

DATES: We must receive comments on 

this supplemental NPRM by September 

24, 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: 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 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; 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: 

Kelly McGuckin, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: (425) 917– 

6490; fax: (425) 917–6590; email: Kelly.

McGuckin@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–2005–22523; Directorate Identifier 

2005–NM–058–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 issued an NPRM to amend 14 CFR 

part 39 to include an AD that would 

apply to certain The Boeing Company 

Model 767–200, –300, –300F, and 

–400ER series airplanes. That NPRM 

published in the Federal Register on 

September 27, 2005 (70 FR 56386). That 

NPRM proposed to require drilling a 

drain hole in the flanged tubes for the 

E1A and E1B elevator control cable aft 

pressure seals; doing repetitive 

inspections for dirt, loose particles, or 

blockage of the flanged tube and drain 

hole for the E1A and E1B elevator 

control cable aft pressure seals and 

corrective action if necessary; replacing 

the aft air-intake duct assembly with a 

new or modified aft air-intake duct 

assembly and installing a dripshield; 

and installing gutters on the horizontal 

stabilizer center section and modifying 

the side brace fittings. 

Actions Since Previous NPRM (70 FR 

56386, September 27, 2005) Was Issued 

Since we issued the previous NPRM 

(70 FR 56386, September 27, 2005), we 

have received reports of elevator control 

restrictions from operators who had 

implemented the actions specified in 

the previous NPRM. 

Since we issued the previous NPRM 

(70 FR 56386, September 27, 2005), we 

have also received revised and new 

service information. 

We have reviewed Boeing Service 

Bulletin 767–27–0204, Revision 2, dated 

August 16, 2011 (for Model 767–200, 

–300, and –300F series airplanes); and 

Boeing Service Bulletin 767–27–0205, 

Revision 2, dated August 30, 2011 (for 

Model 767–400ER series airplanes). We 

referred to Boeing Service Bulletin 767– 

27–0204, dated January 27, 2005; and 

Boeing Service Bulletin 767–27–0205, 

dated January 27, 2005; as the 

appropriate sources of service 

information for accomplishing the 

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47564 Federal Register / Vol. 77, No. 154 / Thursday, August 9, 2012 / Proposed Rules 

actions proposed in paragraph (g) of the 

previous NPRM (70 FR 56386, 

September 27, 2005). Revision 2 of this 

service information revises the type of 

inspection from a detailed inspection to 

a general visual inspection, and also 

revises the compliance times by basing 

one time on the accomplishment of 

Boeing Service Bulletin 767–27A0219. 

Boeing Service Bulletin 767–27–0204, 

Revision 2, dated August 16, 2011, 

revises the effectivity to specify line 

numbers 225, 226, 228 through 717, and 

719 through 971, except airborne 

warning and control system (AWACS) 

airplanes (previous effectivity was line 

numbers 225, 226 and 228 through 

9999). Boeing Service Bulletin 767–27– 

0205, Revision 2, dated August 30, 

2011, also revises the effectivity to 

specify line numbers 758 through 965 

(Revision 2 of this service information 

removes airplanes—the earlier revisions 

specified ‘‘all’’ airplanes). We have 

revised paragraphs (c) and (g) of this 

supplemental NPRM to refer to this 

revised service information. We have 

also added new paragraph (m)(1) to give 

credit for actions done before the 

effective date of the AD using earlier 

versions of Boeing Service Bulletin 767– 

27–0204, Revision 2, dated August 16, 

2011; and Boeing Service Bulletin 767– 

27–0205, Revision 2, dated August 30, 

2011. 

We have also reviewed Boeing Service 

Bulletin 767–27A0224, Revision 1, 

dated December 16, 2011, which 

describes procedures for replacing the 

two existing pressure seal assemblies for 

the left elevator control cables at the aft 

pressure bulkhead. The replacement 

also includes closing existing drain 

holes for airplanes that have drain holes 

in the seal block tubes. Boeing Service 

Bulletin 767–27A0224, Revision 1, 

dated December 16, 2011, specifies that, 

for certain airplanes, the replacement 

eliminates the need for the inspections 

specified in Boeing Service Bulletin 

767–27–0204, Revision 2, dated August 

16, 2011; and Boeing Service Bulletin 

767–27–0205, Revision 2, dated August 

30, 2011. 

We have determined that the 

replacement specified in Boeing Service 

Bulletin 767–27A0224, Revision 1, 

dated December 16, 2011, needs to be 

done to address the identified unsafe 

condition instead of the actions 

proposed in paragraph (f) of the 

previous NPRM (70 FR 56386, 

September 27, 2005). We have not 

retained paragraph (f) of the previous 

NPRM in this supplemental NPRM. The 

effectivity of Boeing Service Bulletin 

767–27A0224, Revision 1, dated 

December 16, 2011, includes line 

numbers 906 through 974, which were 

not in the service information 

referenced in paragraph (f) of the 

previous NPRM. 

We have added new paragraph (h) to 

this supplemental NPRM to propose to 

require the replacement specified in 

Boeing Service Bulletin 767–27A0224, 

Revision 1, dated December 16, 2011, 

for certain airplanes and, for certain 

other airplanes, we have added new 

paragraph (l) in this supplemental 

NPRM to provide the replacement as an 

optional action. We have also added 

new paragraph (m)(2) to this 

supplemental NPRM to give credit for 

actions done in accordance with Boeing 

Alert Service Bulletin 767–27A0224, 

dated June 23, 2011. 

We have also reviewed Boeing Service 

Bulletin 767–49A0035, Revision 2, 

dated June 2, 2006. We referred to 

Boeing Alert Service Bulletin 767– 

49A0035, Revision 1, dated December 

11, 2003, as the appropriate source of 

service information for accomplishing 

the actions proposed in paragraph (h) of 

the previous NPRM (70 FR 56386, 

September 27, 2005). Revision 2 of this 

service bulletin advises operators that it 

is unnecessary to remove the forward 

intake duct. Revision 2 of this service 

bulletin also adds notes and removes 

certain steps to clarify the procedure. 

We have revised paragraph (i) of this 

supplemental NPRM (which 

corresponds to paragraph (h) of the 

previous NPRM) to refer to Boeing 

Service Bulletin 767–49A0035, Revision 

2, dated June 2, 2006. We have added 

new paragraph (m)(3) to this 

supplemental NPRM to give credit for 

doing the applicable actions in 

accordance with Boeing Alert Service 

Bulletin 767–49A0035, Revision 1, 

dated December 11, 2003. 

We have also reviewed Boeing Service 

Bulletin 767–51A0027, Revision 1, 

dated October 12, 2006; and Boeing 

Service Bulletin 767–51A0028, Revision 

1, dated October 12, 2006. We referred 

to Boeing Alert Service Bulletin 767– 

51A0027, dated December 9, 2004; and 

Boeing Alert Service Bulletin 767– 

51A0028, dated December 9, 2004; as 

the appropriate sources of service 

information for accomplishing the 

actions proposed in paragraph (i) of the 

previous NPRM (70 FR 56386, 

September 27, 2005). Revision 1 of this 

service information adds a high 

frequency eddy current inspection for 

cracks as an option to a certain dye 

penetrant inspection, and adds a 

corrective action for those inspections, 

i.e., oversizing the hole. Revision 1 of 

this service information also adds an 

option to install the gutter as a onepiece assembly. We have revised 

paragraph (j) of this supplemental 

NPRM (which corresponds to paragraph 

(i) of the previous NPRM) to refer to 

Boeing Service Bulletin 767–51A0027, 

Revision 1, dated October 12, 2006; and 

to Boeing Service Bulletin 767– 

51A0028, Revision 1, dated October 12, 

2006. We have added new paragraph 

(m)(4) to this supplemental NPRM to 

give credit for doing actions in 

accordance with Boeing Alert Service 

Bulletin 767–51A0027, dated December 

9, 2004; and Boeing Alert Service 

Bulletin 767–51A0028, dated December 

9, 2004. 

Comments 

We gave the public the opportunity to 

comment on the previous NPRM (70 FR 

56386, September 27, 2005). The 

following presents the comments 

received on the previous NPRM and the 

FAA’s response to each comment. 

Request To Withdraw the Previous 

NPRM (70 FR 56386, September 27, 

2005) 

Airlines for America, on behalf of its 

member Delta Airlines (Delta), 

requested we withdraw the previous 

NPRM (70 FR 56386, September 27, 

2005). Delta stated that ‘‘the root causes 

of the three noted findings were not 

conclusively identified,’’ and 

withdrawal would be justified by the 

lack of documented blade seal leakage 

in service. Delta noted that the Boeing 

767 fleet has been in operation for over 

20 years and has had relatively few 

instances of stiff controls in the area of 

the modifications proposed by the 

previous NPRM. Delta stated that the 

modifications involve a change in 

design of the aircraft to divert possible 

water intrusion, yet the water intrusion 

was not a concern until the second 

quarter of 2001. Delta indicated that ‘‘it 

seems unlikely that a poor design that 

is not age-related would cause concern 

after so many years of time-tested, safe 

operations.’’ Delta stated that a 

regulatory action to correct a design 

problem that has not been identified 

conclusively is unjustified. 

We disagree with the commenter’s 

request. The in-service events of Model 

767 airplane elevator control restrictions 

were investigated by The Boeing 

Company subsequent to the events 

identified in the previous NPRM (70 FR 

56386, September 27, 2005). One of 

these events included difficulty flaring 

the airplane and a subsequent hard 

landing. These conditions made it 

difficult for the flightcrew to control the 

pitch of the airplane because elevator 

control movements were restricted. The 

investigation included analysis of flight 

data recorder information and onairplane testing. Determining the exact 

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Federal Register / Vol. 77, No. 154 / Thursday, August 9, 2012 / Proposed Rules 47565 

location of suspected icing and 

conclusively identifying a root cause 

was very difficult on in-service 

airplanes as the ice formed at high 

altitudes, and then melted upon landing 

at an airport. In addition, Boeing 

identified the most probable locations of 

the control system freezing, and 

identified the probable locations of 

moisture ingress. Boeing released 

service information as a result of this 

investigation. 

We concur with Boeing’s conclusions 

and the recommendations contained in 

the service information. We have 

determined that an unsafe condition 

exists on the affected airplanes, and is 

likely to exist or develop on other 

airplanes of the same type design. 

Issuance of an AD is the appropriate 

vehicle to correct an unsafe condition. 

No change has been made to this 

supplemental NPRM in this regard. 

Request to Extend Compliance Times 

Airlines for America, on behalf of its 

member UPS, requested we extend the 

compliance time for the replacement 

specified in paragraph (h) of the 

previous NPRM (70 FR 56386, 

September 27, 2005) from 18 to 24 

months. UPS stated that it has not 

accomplished the actions specified in 

the relevant service information because 

there have been no findings at UPS, nor 

have there been any problems related to 

auxiliary power unit (APU) air intake 

duct water leakage causing stiff 

operation of the pitch control system by 

freezing on the associated linear 

variable differential transducer (LVDT). 

UPS stated that continued normal 

maintenance and flight operations 

provide an equivalent level of safety. 

Airlines for America, on behalf of its 

member Delta, requested that we extend 

the compliance time for the 

modification and installation specified 

in paragraph (i) of the previous NPRM 

(70 FR 56386, September 27, 2005) from 

60 to 72 months. Delta stated that the 

proposed compliance time does not fall 

into a routine maintenance opportunity. 

Delta noted again that there have been 

no specific instances of blade seal 

leakage on an in-service aircraft, and 

stated that seal leakage has occurred 

only during a ‘‘wet-down’’ test. Delta 

also stated that Boeing has not indicated 

there is a freezing problem attributed to 

stiff controls from blade seal leakage 

and that the root cause cannot be 

identified conclusively. Delta stated this 

lack of conclusive evidence over 20 

years of operational history should be 

adequate to establish a more amenable 

compliance time. 

We disagree with both requests for 

extensions of the compliance times. 

Since issuance of the previous NPRM 

(70 FR 56386, September 27, 2005), we 

have received several additional reports 

of elevator system restrictions likely 

caused by ice accumulation. The 

compliance times of 18 months 

specified in paragraph (i) and 60 months 

specified in paragraph (j) of this 

supplemental NPRM (which correspond 

to paragraphs (h) and (i) of the previous 

NPRM (70 FR 56386, September 27, 

2005)) are based on our review of the 

manufacturer’s recommended 

compliance times, which are based on 

airplane-level risk assessment and input 

from the lead airline. We have 

determined that these compliance times 

are appropriate to ensure an acceptable 

level of safety for the affected fleet. We 

have not changed this supplemental 

NPRM in this regard. 

Request to Exclude Certain 

Requirements for Freighter Airplanes 

Airlines for America, on behalf of its 

member UPS, requested that we revise 

paragraphs (f) and (g) of the previous 

NPRM (70 FR 56386, September 27, 

2005) to exclude airplanes that do not 

have associated aft galley installations. 

The commenter stated that aft galleys 

are not installed on the Model 767–300F 

(freighter) airplanes in its fleet. 

We disagree. We considered 

excluding freighter airplanes from the 

specified paragraphs of this 

supplemental NPRM. Although a 

leaking aft galley has been determined 

to potentially cause moisture to collect 

and freeze on the elevator control cables 

in this area, other sources of moisture 

were considered. These other sources 

include leaking cargo containers, and 

rain, snow, and ice on cargo containers. 

In light of these other potential moisture 

sources, we determined that paragraphs 

(g) and (h) of this supplemental NPRM 

are also applicable to freighter airplanes; 

paragraph (h) of this supplemental 

NPRM contains the new actions we are 

proposing instead of the action 

proposed in paragraph (g) of the 

previous NPRM (70 FR 56386, 

September 27, 2005). 

Request to Revise Alternative Methods 

of Compliance (AMOC) Section 

Boeing requested we revise the AMOC 

paragraph (i.e., paragraph (k)) of the 

previous NPRM (70 FR 56386, 

September 27, 2005) to include a 

provision to allow repairs to be 

approved by a Boeing Company 

Authorized Representative (AR) who 

has been authorized by the FAA to make 

such findings. 

We agree and have added new 

paragraph (n)(3) to this supplemental 

NPRM accordingly. 

Request to Change Service Information 

Reference 

Delta requested we revise paragraph 

(f) of the previous NPRM (70 FR 56386, 

September 27, 2005) to refer to Boeing 

Service Bulletin 767–27A0192, Revision 

1, dated March 17, 2005. 

We agree that paragraph (f) of the 

previous NPRM (70 FR 56386, 

September 27, 2005) included an 

incorrect reference. However, we have 

not restated that paragraph in this 

supplemental NPRM. We have not 

revised this supplemental NPRM in this 

regard. 

Additional Changes 

We have added a new paragraph (d) 

to this supplemental NPRM to provide 

the Air Transport Association (ATA) of 

America subject codes. These codes are 

added to make this supplemental NPRM 

parallel with other new AD actions. 

We have revised the heading and 

wording for paragraph (m) of this 

supplemental NPRM; this change does 

not affect the intent of that paragraph. 

FAA’s Determination 

We are proposing this supplemental 

NPRM 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. Certain changes described 

above expand the scope of the original 

NPRM. As a result, we have determined 

that it is necessary to reopen the 

comment period to provide additional 

opportunity for the public to comment 

on this supplemental NPRM. 

Proposed Requirements of the 

Supplemental NPRM 

This supplemental NPRM would 

require, depending on airplane 

configuration, repetitive general visual 

inspections for dirt, loose particles, and 

blockage of the flanged tube and drain 

hole for the E1A and E1B elevator 

control cable aft pressure seals, and 

corrective actions if necessary; 

replacement of the two existing pressure 

seal assemblies for the left elevator 

control cables at the aft pressure 

bulkhead; replacement of the aft airintake duct assembly with a new or 

modified aft air-intake duct assembly 

and installation of a dripshield; and 

installation of gutters on the horizontal 

stabilizer center section and 

modification of the side brace fittings, 

including a dye penetrant or high 

frequency eddy current inspection for 

cracking and damage and corrective 

actions if necessary. 

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47566 Federal Register / Vol. 77, No. 154 / Thursday, August 9, 2012 / Proposed Rules 

Differences Between the Proposed AD 

and the Service Information 

Boeing Service Bulletin 767– 

51A0027, Revision 1, dated October 12, 

2006; and Boeing Service Bulletin 767– 

51A0028, Revision 1, dated October 12, 

2006; specify 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 ODA whom we 

have authorized to make those findings. 

Step 8 in Figures 6 and 10 of Boeing 

Service Bulletin 767–51A0027, Revision 

1, dated October 12, 2006; and Boeing 

Service Bulletin 767–51A0028, Revision 

1, dated October 12, 2006; specifies 

hydraulic hose, part number AS115– 

08D0274; this supplemental NPRM 

specifies the correct part number, 

AS115–08D0280. 

For steps 4, 8, and 12 in Figures 6 and 

10 of Boeing Service Bulletin 767– 

51A0027, Revision 1, dated October 12, 

2006; and Boeing Service Bulletin 767– 

51A0028, Revision 1, dated October 12, 

2006: This supplemental NPRM allows 

hydraulic hose, part number AS115– 

08K0280, as an option to part number 

AS115–08D0280. 

For steps 2, 6, and 10 in Figures 6 and 

10 of Boeing Service Bulletin 767– 

51A0027, Revision 1, dated October 12, 

2006; and Boeing Service Bulletin 767– 

51A0028, Revision 1, dated October 12, 

2006: This supplemental NPRM allows 

hydraulic hose, part number AS115– 

06K0274, as an option to part number 

AS115–06D0274. 

Steps 3.B.16 and 3.B.17 of Boeing 

Service Bulletin 767–51A0027, Revision 

1, dated October 12, 2006; and Boeing 

Service Bulletin 767–51A0028, Revision 

1, dated October 12, 2006; specify to do 

a check of the elevator power control 

actuator and a systems test of the 

autopilot system. Those actions would 

not be required by this supplemental 

NPRM because those systems are not 

disturbed during gutter installation. 

Where Note (d) of Figure 8 of Boeing 

Service Bulletin 767–51A0027, Revision 

1, dated October 12, 2006; and Boeing 

Service Bulletin 767–51A0028, Revision 

1, dated October 12, 2006; specifies to 

‘‘install collars on the upper surface of 

the gutter,’’ this supplemental NPRM 

would require that operators install 

these bolts with the bolt heads either up 

or down provided that the bolt head 

direction prevents interference between 

the collars and the hydraulic lines. 

Step 1 of Figure 4 of Boeing Service 

Bulletin 767–49A0035, Revision 2, 

dated June 2, 2006, specifies to install 

the forward air-intake duct. This action 

is not included in this supplemental 

NPRM because it is not necessary for 

operators to remove the forward airintake duct. 

Costs of Compliance 

We estimate that this proposed AD 

affects about 400 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 of the flanged tube and drain 

hole (300 airplanes).

2 work-hours × $85 per hour = $170 per 

inspection cycle.

$0 $170 per inspection 

cycle.

$51,000 per inspection cycle. 

Pressure seal replacement (300 airplanes).7 work-hours × $85 per hour = $595 ...... 261 856 .......................... 256,800 

Aft air-intake duct assembly replacement 

and dripshield installation (358 airplanes).

3 work-hours × $85 per hour = $255 ...... 1,462 1,717 ....................... 614,686 

Horizontal stabilizer gutter installation 

and modification of the side brace fittings (354 airplanes).

12 work-hours × $85 per hour = $1,020 1,902 2,922 ....................... 1,034,388 

We estimate the following costs to do 

any necessary cleaning 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 this cleaning. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Cleaning ................... 1 work-hour × $85 per hour = $85 ................................................................................... $0 $85 

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. 

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Federal Register / Vol. 77, No. 154 / Thursday, August 9, 2012 / Proposed Rules 47567 

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– 

2005–22523; Directorate Identifier 2005– 

NM–058–AD. 

(a) Comments Due Date 

We must receive comments by September 

24, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 767–200, –300, –300F, and –400ER 

series airplanes, certificated in any category; 

as identified in the service information 

specified in paragraphs (c)(1), (c)(2), (c)(3), 

(c)(4), (c)(5), and (c)(6) of this AD. 

(1) Boeing Service Bulletin 767–27A0224, 

Revision 1, dated December 16, 2011. 

(2) Boeing Service Bulletin 767–49A0035, 

Revision 2, dated June 2, 2006. 

(3) Boeing Service Bulletin 767–27–0204, 

Revision 2, dated August 16, 2011. 

(4) Boeing Service Bulletin 767–27–0205, 

Revision 2, dated August 30, 2011. 

(5) Boeing Service Bulletin 767–51A0027, 

Revision 1, dated October 12, 2006. 

(6) Boeing Service Bulletin 767–51A0028, 

Revision 1, dated October 12, 2006. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 27, Flight controls; 49, Airborne 

auxiliary power; 51, Standard practices/ 

structures. 

(e) Unsafe Condition 

This AD was prompted by reports of stiff 

operation of the elevator pitch control system 

and jammed elevator controls. We are issuing 

this AD to prevent moisture from collecting 

and freezing on the elevator control system 

components, which could limit the ability of 

the flightcrew to make elevator control inputs 

and result in reduced controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections and Corrective Actions 

For airplanes identified in Boeing Service 

Bulletin 767–27–0204, Revision 2, dated 

August 16, 2011; and Boeing Service Bulletin 

767–27–0205, Revision 2, dated August 30, 

2011: At the applicable time specified in 

paragraph (g)(1) or (g)(2) of this AD, do a 

general visual inspection for dirt, loose 

particles, and blockage of the flanged tube 

and drain hole for the E1A and E1B elevator 

control cable aft pressure seals, and all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 767–27–0204, 

Revision 2, dated August 16, 2011 (for Model 

767–200, –300, and –300F series airplanes); 

or Boeing Service Bulletin 767–27–0205, 

Revision 2, dated August 30, 2011 (for Model 

767–400ER series airplanes). Do all 

applicable corrective actions before further 

flight. Repeat the inspection thereafter at 

intervals not to exceed 24 months. 

(1) For airplanes on which Boeing Service 

Bulletin 767–27A0219 has been done as of 

the effective date of this AD: Do the 

inspection at the time specified in paragraph 

(g)(1)(i) or (g)(1)(ii) of this AD, whichever 

occurs later. 

(i) Within 24 months after doing the 

actions specified in Boeing Service Bulletin 

767–27A0219. 

(ii) Within 6 months after the effective date 

of this AD. 

(2) For airplanes on which Boeing Service 

Bulletin 767–27A0219 has not been done as 

of the effective date of this AD: Do the 

inspection at the time specified in paragraph 

(g)(2)(i) or (g)(2)(ii) of this AD, whichever 

occurs later. 

(i) Within 24 months after the effective 

date of this AD. 

(ii) Within 24 months since the date of 

issuance of the original airworthiness 

certificate or the date of issuance of the 

original export certificate of airworthiness. 

(h) Replacement—Pressure Seal Assemblies 

For Group 1, Configuration 1–2 airplanes; 

Group 2, Configuration 1 airplanes; and 

Group 4, Configuration 1–2 airplanes; as 

identified in Boeing Service Bulletin 767– 

27A0224, Revision 1, dated December 16, 

2011: Within 24 months after the effective 

date of this AD, replace the two existing 

pressure seal assemblies for the left elevator 

control cables at the aft pressure bulkhead, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

27A0224, Revision 1, dated December 16, 

2011. Accomplishing this replacement 

terminates the inspections required by 

paragraph (g) of this AD. 

(i) Replacement—Air-Intake Duct Assembly 

and Installation—Dripshield 

For airplanes identified in Boeing Service 

Bulletin 767–49A0035, Revision 2, dated 

June 2, 2006: Within 18 months after the 

effective date of this AD, replace the aft airintake duct assembly with a new or modified 

aft air-intake duct assembly and install a 

dripshield, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–49A0035, Revision 2, 

dated June 2, 2006, except as provided by 

paragraph (k)(1) of this AD. 

(j) Gutter Installation and Side Brace 

Modification 

For airplanes identified in Boeing Service 

Bulletin 767–51A0027, Revision 1, dated 

October 12, 2006; and Boeing Service 

Bulletin 767–51A0028, Revision 1, dated 

October 12, 2006: Within 60 months after the 

effective date of this AD, install gutters on 

the horizontal stabilizer center section, and 

modify the side brace fittings, including 

doing a dye penetrant or high frequency eddy 

current inspection for cracking and damage 

of the drain hole and all applicable corrective 

actions, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–51A0027, Revision 1, 

dated October 12, 2006 (for Model 767–200, 

–300, and –300F series airplanes); or Boeing 

Service Bulletin 767–51A0028, Revision 1, 

dated October 12, 2006 (for Model 767– 

400ER series airplanes); except as provided 

by paragraphs (k)(2), (k)(3), (k)(4), (k)(5), 

(k)(6), and (k)(7) of this AD. 

(k) Exceptions to Service Information 

(1) Where Step 1 of Figure 4 of Boeing 

Service Bulletin 767–49A0035, Revision 2, 

dated June 2, 2006, specifies installing the 

forward air-intake duct, that installation is 

not required by this AD. 

(2) Where Boeing Service Bulletin 767– 

51A0027, Revision 1, dated October 12, 2006; 

and Boeing Service Bulletin 767–51A0028, 

Revision 1, dated October 12, 2006; specify 

to contact Boeing for appropriate action: 

Before further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (n) of this AD. 

(3) Where step 8 in Figures 6 and 10 of 

Boeing Service Bulletin 767–51A0027, 

Revision 1, dated October 12, 2006; and 

Boeing Service Bulletin 767–51A0028, 

Revision 1, dated October 12, 2006; specify 

hydraulic hose, part number AS115– 

08D0274, the correct part number is AS115– 

08D0280. 

(4) For steps 4, 8, and 12 in Figures 6 and 

10 of Boeing Service Bulletin 767–51A0027, 

Revision 1, dated October 12, 2006; and 

Boeing Service Bulletin 767–51A0028, 

Revision 1, dated October 12, 2006: 

Hydraulic hose, part number AS115– 

08K0280, is an option to part number 

AS115–08D0280. 

(5) For steps 2, 6, and 10 in Figures 6 and 

10 of Boeing Service Bulletin 767–51A0027, 

Revision 1, dated October 12, 2006; and 

Boeing Service Bulletin 767–51A0028, 

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47568 Federal Register / Vol. 77, No. 154 / Thursday, August 9, 2012 / Proposed Rules 

Revision 1, dated October 12, 2006: 

Hydraulic hose, part number AS115– 

06K0274, is an option to part number 

AS115–06D0274. 

(6) Steps 3.B.16 and 3.B.17 of Boeing 

Service Bulletin 767–51A0027, Revision 1, 

dated October 12, 2006; and Boeing Service 

Bulletin 767–51A0028, Revision 1, dated 

October 12, 2006; are not required by this 

AD. 

(7) Where Note (d) of Figure 8 of Boeing 

Service Bulletin 767–51A0027, Revision 1, 

dated October 12, 2006; and Boeing Service 

Bulletin 767–51A0028, Revision 1, dated 

October 12, 2006; specifies to ‘‘install collars 

on the upper surface of the gutter,’’ this AD 

requires that operators install these bolts 

with the bolt heads either up or down 

provided that the bolt head direction 

prevents interference between the collars and 

the hydraulic lines. 

(l) Optional Replacement—Pressure Seal 

Assemblies 

For Group 1, Configuration 3–4 airplanes; 

Group 2, Configuration 2–3 airplanes; Group 

3 airplanes; and Group 4, Configuration 3–4 

airplanes; as identified in Boeing Service 

Bulletin 767–27A0224, Revision 1, dated 

December 16, 2011: Replacing the two 

existing pressure seal assemblies for the left 

elevator control cables at the aft pressure 

bulkhead, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–27A0224, Revision 1, 

dated December 16, 2011, terminates the 

inspections required by paragraph (g) of this 

AD. 

(m) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if the actions were performed before the 

effective date of this AD using the applicable 

service information in paragraph (m)(1)(i) or 

(m)(1)(ii) of this AD. 

(i) For Model 767–200, –300, and –300F 

series airplanes: Boeing Service Bulletin 767– 

27–0204, dated January 27, 2005; or Boeing 

Service Bulletin 767–27–0204, Revision 1, 

dated February 12, 2009. 

(ii) For Model 767–400ER series airplanes: 

Boeing Service Bulletin 767–27–0205, dated 

January 27, 2005; or Boeing Service Bulletin 

767–27–0205, Revision 1, dated February 12, 

2009. 

(2) This paragraph provides credit for the 

actions required by paragraphs (h) and (l) of 

this AD, if the actions were performed before 

the effective date of this AD using Boeing 

Alert Service Bulletin 767–27A0224, dated 

June 23, 2011. 

(3) This paragraph provides credit for the 

actions required by paragraph (i) of this AD, 

if the actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 767–49A0035, Revision 1, 

dated December 11, 2003. 

(4) This paragraph provides credit for the 

actions required by paragraph (j) of this AD, 

if the actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 767–51A0027, dated 

December 9, 2004; or Boeing Alert Service 

Bulletin 767–51A0028, dated December 9, 

2004. 

(n) 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. 

(o) Related Information 

(1) For more information about this AD, 

contact Kelly McGuckin, Aerospace 

Engineer, Systems and Equipment Branch, 

ANM–130S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: (425) 917– 

6490; fax: (425) 917–6590; email: Kelly.

McGuckin@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; 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 July 31, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–19532 Filed 8–8–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0829; Directorate 

Identifier 2012–CE–024–AD] 

RIN 2120–AA64 

Airworthiness Directives; Hawker 

Beechcraft Corporation 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 

Hawker Beechcraft Corporation Model 

G58 airplanes. This proposed AD was 

prompted by notification from Hawker 

Beechcraft Corporation that certain 

affected aircraft were produced with the 

incorrect gauge wiring installed. This 

proposed AD would require 

replacement of the incorrect gauge 

wiring with the correct wiring required 

by type design and the aircraft’s circuit 

protection. We are proposing this AD to 

correct the unsafe condition on these 

products. 

DATES: We must receive comments on 

this proposed AD by September 24, 

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 Hawker 

Beechcraft Corporation, B091–A04, 

10511 E. Central Ave., Wichita, Kansas 

67206; telephone: 1 (800) 429–5372 or 

(316) 676–3140; fax: (316) 676–8027; 

email: tmdc@hawkerbeechcraft.com; or 

Internet: http:// 

www.hawkerbeechcraft.com/ 

customer_support/ 

technical_and_field_support/. 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 

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