This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

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new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

17285 

Vol. 78, No. 55 

Thursday, March 21, 2013 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22523; Directorate 

Identifier 2005–NM–058–AD; Amendment 

39–17379; AD 2013–05–07] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 767 

airplanes. This AD was prompted by 

reports of stiff operation of the elevator 

pitch control system and jammed 

elevator controls. This AD requires 

replacing pressure seal assemblies; 

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. 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. 

DATES: This AD is effective April 25, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of April 25, 2013. 

ADDRESSES: 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

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: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to include an 

airworthiness directive (AD) that would 

apply to the specified products. That 

SNPRM published in the Federal 

Register on August 9, 2012 (77 FR 

47563). The original NPRM (70 FR 

56386, September 27, 2005) 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. The SNPRM proposed to 

revise the NPRM by requiring 

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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the SNPRM (77 FR 47563, 

August 9, 2012) and the FAA’s response 

to each comment. One commenter, 

Natalia Budyldina, stated the SNPRM is 

significant since it is related to airplane 

safety, would let the pilot better control 

the airplane, and would reduce airplane 

delays due to technical problems. 

Request To Allow Installing New or 

Modified Aft Air-Intake Duct 

Assemblies 

UPS requested that we revise 

paragraph (i) of the SNPRM (77 FR 

47563, August 9, 2012) to clarify if 

operators are allowed to install a ‘‘new 

or reworked duct’’ on all affected 

airplanes or if operators must strictly 

follow the service information. UPS 

stated that paragraph (i) of the SNPRM 

requires installation of a ‘‘new or 

modified’’ aft air-intake duct assembly 

in accordance with Boeing Service 

Bulletin 767–49A0035, Revision 2, 

dated June 2, 2006, which specifies to 

install a new duct assembly on the first 

airplane modified in an operator’s fleet 

and to install reworked duct assemblies 

on the operator’s remaining fleet. 

We agree that installing either new or 

reworked duct assemblies on all 

airplanes in an operator’s fleet addresses 

the identified unsafe condition. We 

have revised paragraph (i) of this AD to 

refer to new paragraph (k)(8) of this AD, 

which states that where Boeing Service 

Bulletin 767–49A0035, Revision 2, 

dated June 2, 2006, specifies installing 

a new aft air-intake duct assembly on 

the first airplane in each operator’s fleet 

and installing a reworked aft air-intake 

duct assembly on all remaining 

airplanes in each operator’s fleet, this 

AD requires installing either a new or 

reworked aft air-intake duct assembly 

on all airplanes. 


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Request To Extend Compliance Time 

Boeing requested that, for airplanes 

on which Boeing Service Bulletin 767– 

27A0219 has been done, we extend the 

compliance time specified in paragraph 

(g)(1)(ii) of the SNPRM (77 FR 47563, 

August 9, 2012) from 6 months to 24 

months after the effective date of the AD 

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. Boeing stated 

that the 24-month compliance time, 

which will allow operators to 

incorporate the drain hole inspection 

into a standard maintenance interval, is 

supported by the Boeing analysis in 

which the compliance recommendation 

for 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, was formulated. 

We agree. We have determined that, 

for airplanes on which Boeing Service 

Bulletin 767–27A0219 has been done as 

of the effective date of this AD, a 

compliance time of within 24 months 

will provide an acceptable level of 

safety for accomplishing the inspection 

required by paragraph (g) of this AD. We 

have revised paragraph (g)(1) of this AD 

accordingly (and removed paragraphs 

(g)(1)(i) and (g)(1)(ii) of the SNPRM (77 

FR 47563, August 9, 2012)). 

Request To Add Exception for Group 4 

Airplanes Identified in Boeing Service 

Bulletin 767–27A0224, Revision 1, 

Dated December 16, 2011 

Boeing requested that we add an 

exception for Group 4 airplanes 

identified in Boeing Service Bulletin 

767–27A0224, Revision 1, dated 

December 16, 2011, to allow operators 

that have replaced the configuration 

having two seal plates (part numbers 

(P/Ns) 255T4847–1 and 65–28174–1) 

with the configuration having one seal 

plate (P/N 255T4847–5) to omit the 

removal/installation of the kept part, 

named ‘‘SEAL PLATE ASSEMBLY,’’ 

while performing Figures 7 through 10 

of Boeing Service Bulletin 767– 

27A0224, Revision 1, dated December 

16, 2011. Boeing also stated that Group 

1 though 3 airplanes can use the twopart configuration as an alternative to 

the one-part configuration while 

performing Figure 1 and Figures 4 

through 6 of Boeing Service Bulletin 

767–27A0224, Revision 1, dated 

December 16, 2011. Boeing stated the 

installation of P/N 255T4847–5 is 

equivalent to the combination of P/Ns 

255T4847–1 and 65–28174–1 for the 

purposes of Boeing Service Bulletin 

767–27A0224, Revision 1, dated 

December 16, 2011. 

We agree to add an exception to this 

AD, for the reasons provided by the 

commenter. We have revised paragraphs 

(h) and (l) of this AD to refer to new 

paragraphs (k)(9) and (k)(10) of this AD: 

• Paragraph (k)(9) of this AD 

specifies, for Group 4 airplanes, as 

identified in Boeing Service Bulletin 

767–27A0224, Revision 1, dated 

December 16, 2011, that where Figures 

7 through 10 of Boeing Service Bulletin 

767–27A0224, Revision 1, dated 

December 16, 2011, specify to replace 

the seal plate assembly, this AD allows 

replacing the configuration having two 

seal plates, P/Ns 255T4847–1 and 65– 

28174–1, with the configuration having 

one seal plate, P/N 255T4847–5. 

• Paragraph (k)(10) to this AD 

specifies, for Group 1 through 3 

airplanes, as identified in Boeing 

Service Bulletin 767–27A0224, Revision 

1, dated December 16, 2011, that where 

Figures 1 and Figures 4 through 6 of 

Boeing Service Bulletin 767–27A0224, 

Revision 1, dated December 16, 2011, 

specify to replace the seal plate, this AD 

allows replacing the configuration 

having one seal plate, P/N 255T4847–5, 

with the configuration having two seal 

plates, P/Ns 255T4847–1 and 65– 

28174–1. 

Request for Exception To Allow 

Installation of Clamp 

Boeing requested that we allow 

installation of a clamp, P/N AN735–( ), 

having a larger diameter than the clamp 

specified in steps 8 and 9 of Figure 4 

and steps 8 and 9 of Figure 8 of Boeing 

Service Bulletin 767–27A0224, Revision 

1, dated December 16, 2011. Boeing 

stated that the existing flanged tube may 

have a repair that increases its diameter 

and that installation of a clamp, P/N 

AN735–( ), of increased diameter would 

be necessary in order to meet the clamp 

installation specifications. 

We agree to allow installation of the 

larger clamps, P/N AN735–( ), as 

requested. We have revised paragraphs 

(h) and (l) to refer to new paragraph 

(k)(11) of this AD, which specifies that 

where steps 8 and 9 of Figure 4 and 

steps 8 and 9 of Figure 8 of Boeing 

Service Bulletin 767–27A0224, Revision 

1, dated December 16, 2011, specify 

installing clamp P/N AN735–16, this 

AD allows, for airplanes having 

increased diameter of the flanged tube 

due to a repair, installation of a clamp, 

P/N AN735–( ), that has a larger 

diameter than P/N AN735–16. 

Request To Allow Substitute Fasteners 

Boeing requested that we allow 

substitute fasteners (bolts) for the bolts 

specified in Figures 6 and 10 of Boeing 

Service Bulletin 767–27A0224, Revision 

1, dated December 16, 2011. Boeing 

stated that bolts, P/N BACB30NT3K( ), 

BACB30LK3–( ), BACB30ZG3–( ), and 

NAS623–3–( ), are substitutes for the 

bolts specified in steps 1 and 4 of Figure 

6 and steps 1 and 4 of Figure 10 of 

Boeing Service Bulletin 767–27A0224, 

Revision 1, dated December 16, 2011. 

Boeing stated that airplanes were 

delivered with those other equivalent 

part numbers and that the structural 

repair manual may not specify that 

these bolts are acceptable substitutes. 

We agree to add an exception to this 

AD for the reason provided by the 

commenter. We have revised paragraphs 

(h) and (l) to refer to new paragraph 

(k)(12) of this AD, which specifies that 

where steps 1 and 4 of Figure 6 and 

steps 1 and 4 of Figure 10 of Boeing 

Service Bulletin 767–27A0224, Revision 

1, dated December 16, 2011, specify 

installing bolts, this AD allows 

installation of bolts having P/N 

BACB30NT3K( ), BACB30LK3–( ), 

BACB30ZG3–( ), or NAS623–3–( ). 

Request To Allow Exception for 

Operators That Have Done a 

Replacement 

Boeing requested that we add an 

exception for airplanes identified as 

Group 1, Configuration 2 through 4 

airplanes, Group 2 and 3 airplanes, and 

Group 4, Configuration 2 through 4 

airplanes, in Boeing Service Bulletin 

767–27A0224, Revision 1, dated 

December 16, 2011 (we referred to that 

service bulletin as the appropriate 

source of service information for 

accomplishing the replacement required 

by paragraph (h) of the SNPRM (77 FR 

47563, August 9, 2012), and the optional 

replacement specified in paragraph (l) of 

the SNPRM). Boeing stated the 

exception would allow operators that 

replaced a flanged tube with a new 

flanged tube as a repair (after 

accomplishing Boeing Service Bulletin 

767–27A0224, Revision 1, dated 

December 16, 2011) to install the 

replacement flanged tube without 

restoring the drain hole and clamp. 

Boeing stated that replacement flanged 

tubes do not have a pre-drilled drain 

hole, and it is unnecessary to restore the 

configuration with the drain hole and 

clamp to cover the drain hole. 

We disagree with the request to add 

an exception to this AD for operators 

that have accomplished the replacement 

specified in paragraph (h) or (l) of this 

AD. Boeing did not submit information 

(e.g., what specific replacement parts 

are acceptable) to substantiate that this 

method of compliance with paragraphs 

(h) and (l) of this AD addresses the 


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identified unsafe condition. Once we 

issue this AD, any person may request 

approval of an AMOC under the 

provisions of paragraph (n) of this AD. 

We have not changed this AD in this 

regard. 

Request To Confirm Credit for a Certain 

Boeing Service Bulletin 

United Airlines requested we confirm 

that credit is provided for previous 

accomplishment of Boeing Service 

Bulletin 767–51A0027, Revision 1, 

dated October 12, 2006. United Airlines 

noted that paragraph (m)(4) of the 

SNPRM (77 FR 47563, August 9, 2012) 

provides credit for Boeing Alert Service 

Bulletin 767–51A0027, dated December 

9, 2004. 

We agree to clarify. This AD does 

provide credit for previous 

accomplishment (i.e., before the 

effective date of this AD) of Boeing 

Service Bulletin 767–51A0027, Revision 

1, dated October 12, 2006 (the 

appropriate source of service 

information for certain Model 767–200, 

–300, and –300F series airplanes for 

accomplishing the actions required by 

paragraph (j) of this AD). Paragraph (f) 

of this AD states: ‘‘Comply with this AD 

within the compliance times specified, 

unless already done.’’ The intent of 

paragraph (f) of this AD is to allow 

credit for previous accomplishment of 

the service information required by the 

AD. 

For previous issues of required 

service information, each AD specifies 

in a separate paragraph whether credit 

is given for those previous issues. 

Paragraph (m)(4) of this AD provides 

credit for Boeing Alert Service Bulletin 

767–51A0027, dated December 9, 2004, 

which is the previous issue of the 

required service bulletin, Boeing Service 

Bulletin 767–51A0027, Revision 1, 

dated October 12, 2006. We have not 

changed this AD in this regard. 

Request To Clarify Paragraphs (g) and 

(h) of the SNPRM (77 FR 47563, August 

9, 2012) 

UPS requested that we clarify the 

requirements of paragraphs (g) and (h) 

of the SNPRM (77 FR 47563, August 9, 

2012). UPS stated that paragraph (g) of 

the SNPRM requires inspections in 

accordance with the work instructions 

contained in Boeing Service Bulletin 

767–27–0204, Revision 2, dated August 

16, 2011, and that Boeing Service 

Bulletin 767–27–0204, Revision 2, dated 

August 16, 2011, lists Boeing Service 

Bulletin 767–27A0219, Revision 1, 

dated February 12, 2009, as a 

‘‘concurrent requirement.’’ UPS asked if 

the intent of paragraph (g) of the 

SNPRM is to mandate the inspections 

without the ‘‘concurrent requirement’’ 

of the modification specified in Boeing 

Service Bulletin 767–27A0219, Revision 

1, dated February 12, 2009. UPS stated 

that if the intent is to require the 

inspections and the modifications, then 

paragraph (h) of the SNPRM should 

read: ‘‘Accomplishing this replacement 

terminates the inspections and 

modification required by paragraph (g) 

of this AD.’’ 

We agree to clarify. Paragraph (g) of 

this AD requires that inspections 

specified in Boeing Service Bulletin 

767–27–0204, Revision 2, dated August 

16, 2011, be done. The compliance time 

for doing those inspections is dependent 

on whether or not any revision of 

‘‘Boeing Service Bulletin 767–27A0219’’ 

has been done, as specified in 

paragraphs (g)(1) and (g)(2) of this AD; 

however, paragraph (g) of this AD does 

not require that the modification 

specified in Boeing Service Bulletin 

767–27A0219, Revision 1, dated 

February 12, 2009, must be done. We 

have not changed this AD in this regard. 

Request for Flexibility in Use of 

Abrasive 

UPS requested that we allow 

flexibility in the use of abrasive 

specified in Figure 5 of Boeing Service 

Bulletin 767–27A0224, Revision 1, 

dated December 16, 2011. UPS stated 

that paragraph (h) of the SNPRM (77 FR 

47563, August 9, 2012) would require 

accomplishment of that service bulletin. 

(Paragraph (l) of the SNPRM would also 

require that service bulletin, if the 

actions in paragraph (l) of the SNPRM 

are done.) UPS stated that Figure 5 

specifies to use an abrasive to prepare 

for adhesive application and that ‘‘80- 

grit is recommended.’’ UPS also noted 

that Figure 5 refers to standard overhaul 

practices manual (SOPM) 20–50–12 for 

adhesive mixing and surface cleaning. 

UPS asked if operators are allowed the 

flexibility offered by the SOPM. 

We agree that there is flexibility in the 

use of abrasive specified in Figure 5 of 

Boeing Service Bulletin 767–27A0224, 

Revision 1, dated December 16, 2011. 

There is no requirement in this AD that 

mandates the use of 80-grit abrasive. As 

noted by the commenter, Figure 5 of 

Boeing Service Bulletin 767–27A0224, 

Revision 1, dated December 16, 2011, 

only recommends the use of 80-grit 

abrasive and includes a reference to 

SOPM 20–50–12. Similarly, Figures 4, 8, 

and 9 of Boeing Service Bulletin 767– 

27A0224, Revision 1, dated December 

16, 2011, only recommend the use of 80- 

grit abrasive. Operators may use an 

abrasive of the specific grit referenced in 

SOPM 20–50–12 to accomplish the 

actions specified in steps 1 and 2 of 

Figures 4, 5, 8, and 9 of Boeing Service 

Bulletin 767–27A0224, Revision 1, 

dated December 16, 2011. We have not 

changed this AD in this regard. 

Request To Revise Effectivity Listed in 

the Preamble of the SNPRM (77 FR 

47563, August 9, 2012) 

Boeing requested that we revise the 

effectivity for Boeing Service Bulletin 

767–27–0204, Revision 2, dated August 

16, 2011, specified in the ‘‘Actions 

Since Previous NPRM (70 FR 56386, 

September 27, 2005) was Issued’’ 

section of the preamble of the SNPRM 

(77 FR 47563, August 9, 2012). Boeing 

stated that the effectivity listed in the 

SNPRM should be revised to include 

line numbers 972 through 974 to match 

the effectivity listed in Boeing Service 

Bulletin 767–27–0204, Revision 2, dated 

August 16, 2011. 

We acknowledge that the effectivity of 

Boeing Service Bulletin 767–27–0204, 

Revision 2, dated August 16, 2011, is 

line numbers 225, 226, 228 through 717, 

and 719 through 971, except airborne 

warning and control system (AWACS) 

airplanes; and line numbers 972 through 

974. However, the ‘‘Actions Since 

Previous NPRM (70 FR 56386, 

September 27, 2005) was Issued’’ 

section of the SNPRM (77 FR 47563, 

August 9, 2012) is not restated in this 

AD. We have not changed this AD in 

this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously— 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM (77 FR 

47563, August 9, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM (77 FR 47563, 

August 9, 2012). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of the AD. 

Costs of Compliance 

We estimate that this AD affects about 

400 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


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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 

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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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): 

2013–05–07 The Boeing Company: 

Amendment 39–17379; Docket No. 

FAA–2005–22523; Directorate Identifier 

2005–NM–058–AD. 

(a) Effective Date 

This AD is effective April 25, 2013. 

(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 Bulletins 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; and 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. 


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(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: Within 24 

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 and 2 

airplanes; Group 2, Configuration 1 airplanes; 

and Group 4, Configuration 1 and 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, except as provided 

by paragraphs (k)(9), (k)(10), (k)(11), and 

(k)(12) of this AD. 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 

paragraphs (k)(1) and (k)(8) 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 (P/N) 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, P/N AS115–08K0280, is an 

option to P/N 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, 

Revision 1, dated October 12, 2006: 

Hydraulic hose, P/N AS115–06K0274, is an 

option to P/N 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. 

(8) Where Boeing Service Bulletin 767– 

49A0035, Revision 2, dated June 2, 2006, 

specifies installing a new aft air-intake duct 

assembly on the first airplane in each 

operator’s fleet and installing a reworked aft 

air-intake duct assembly on all remaining 

airplanes in each operator’s fleet, this AD 

requires installing either a new or reworked 

aft air-intake duct assembly on all airplanes. 

(9) For Group 4 airplanes, as identified in 

Boeing Service Bulletin 767–27A0224, 

Revision 1, dated December 16, 2011: Where 

Figures 7 through 10 of Boeing Service 

Bulletin 767–27A0224, Revision 1, dated 

December 16, 2011, specify to replace the 

seal plate assembly, this AD allows replacing 

the configuration having two seal plates, P/ 

Ns 255T4847–1 and 65–28174–1, with the 

configuration having one seal plate, P/N 

255T4847–5. 

(10) For Group 1 through 3 airplanes, as 

identified in Boeing Service Bulletin 767– 

27A0224, Revision 1, dated December 16, 

2011: Where Figures 1 and Figures 4 through 

6 of Boeing Service Bulletin 767–27A0224, 

Revision 1, dated December 16, 2011, specify 

to replace the seal plate, this AD allows 

replacing the configuration having one seal 

plate, P/N 255T4847–5 with the 

configuration having two seal plates, P/Ns 

255T4847–1 and 65–28174–1. 

(11) Where steps 8 and 9 of Figure 4 and 

steps 8 and 9 of Figure 8 of Boeing Service 

Bulletin 767–27A0224, Revision 1, dated 

December 16, 2011, specify installing clamp 

P/N AN735–16, this AD allows, for airplanes 

having increased diameter of the flanged tube 

due to a repair, installation of a clamp, P/N 

AN735–( ), that has a larger diameter than P/ 

N AN735–16. 

(12) Where steps 1 and 4 of Figure 6 and 

steps 1 and 4 of Figure 10 of Boeing Service 

Bulletin 767–27A0224, Revision 1, dated 

December 16, 2011, specify installing bolts, 

this AD allows installation of bolts having P/ 

N BACB30NT3K( ), BACB30LK3–( ), 

BACB30ZG3–( ), or NAS623–3–( ). 

(l) Optional Replacement—Pressure Seal 

Assemblies 

For Group 1, Configuration 3 and 4 

airplanes; Group 2, Configuration 2 and 3 

airplanes; Group 3 airplanes; and Group 4, 

Configuration 3 and 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, except 

as provided by paragraphs (k)(9), (k)(10), 

(k)(11), and (k)(12) of this AD, 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, which are not 

incorporated by reference. 

(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. 


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17290 Federal Register / Vol. 78, No. 55 / Thursday, March 21, 2013 / Rules and Regulations 

(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, which is not incorporated by 

reference. 

(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, which is not 

incorporated by reference. 

(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 (for Model 767–200, –300, 

and –300F series airplanes); or Boeing Alert 

Service Bulletin 767–51A0028, dated 

December 9, 2004 (for Model 767–400ER 

series airplanes); which are not incorporated 

by reference. 

(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 

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. 

(p) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

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

Revision 2, dated August 16, 2011. 

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

Revision 2, dated August 30, 2011. 

(iii) Boeing Service Bulletin 767–27A0224, 

Revision 1, dated December 16, 2011. 

(iv) Boeing Service Bulletin 767–49A0035, 

Revision 2, dated June 2, 2006. 

(v) Boeing Service Bulletin 767–51A0027, 

Revision 1, dated October 12, 2006. 

(vi) Boeing Service Bulletin 767–51A0028, 

Revision 1, dated October 12, 2006. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

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

5680; Internet https:// 

www.myboeingfleet.com. 

(4) You may view this 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on February 

28, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–05588 Filed 3–20–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0847; Directorate 

Identifier 2008–NM–056–AD; Amendment 

39–17375; AD 2013–05–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 777–200, 

–200LR, –300, and –300ER series 

airplanes. This AD was prompted by 

fuel system reviews conducted by the 

manufacturer. This AD requires doing 

an inspection to identify the part 

number of the motor-operated valve 

(MOV) actuators of the main and center 

fuel tanks; replacing certain MOV 

actuators with new MOV actuators; and 

measuring the electrical resistance of 

the bond from the adapter plate to the 

airplane structure, and doing corrective 

actions if necessary. We are issuing this 

AD to prevent electrical current from 

flowing through an MOV actuator into 

a fuel tank, which could create a 

potential ignition source inside the fuel 

tank. This condition, in combination 

with flammable fuel vapors, could result 

in a fuel tank explosion and consequent 

loss of the airplane. 

DATES: This AD is effective April 25, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of April 25, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 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, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, Seattle 

Aircraft Certification Office (ACO), 

FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6509; 

fax: 425–917–6590; email: 

rebel.nichols@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to include an 


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