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

13048 

Vol. 72, No. 53 

Tuesday, March 20, 2007 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27619; Directorate 

Identifier 2005–NM–164–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 777 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Boeing Model 777 airplanes. 

This proposed AD would require 

repetitive measurements of the freeplay 

of certain joints of the trailing edge flap 

supports; repetitive lubrication of the 

support joints; and related investigative 

and corrective actions if necessary. The 

proposed AD also provides for 

modifying certain components of the 

trailing edge flap supports, which 

would extend the intervals for the 

repetitive measurements, and revising 

the maintenance practices of the 

maintenance planning data document. 

This proposed AD results from reports 

of excessive wear of the pins, bushings, 

and bearings, and corrosion at the joints 

of the outboard trailing edge flap 

supports. We are proposing this AD to 

prevent wear and corrosion at the flap 

support joints, which could result in 

loss of the trailing edge flap and 

possible loss of control of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 4, 2007. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for the service 

information identified in this proposed 

AD. 

FOR FURTHER INFORMATION CONTACT: Gary 

Oltman, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6443; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include the docket 

number ‘‘FAA–2007–27619; Directorate 

Identifier 2005–NM–164–AD’’ at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. We will consider all 

comments received by the closing date 

and may amend the proposed AD in 

light of those comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 

Using the search function of that Web 

site, anyone can find and read the 

comments in any of our dockets, 

including the name of the individual 

who sent the comment (or signed the 

comment on behalf of an association, 

business, labor union, etc.). You may 

review DOT’s complete Privacy Act 

Statement in the Federal Register 

published on April 11, 2000 (65 FR 

19477–78), or you may visit http:// 

dms.dot.gov. 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

Discussion 

We have received reports of excessive 

wear of the pins, bushings, and 

bearings, and corrosion at certain 

support joints on Boeing Model 777 

airplanes. An operator investigating an 

unrelated issue during heavy 

maintenance first discovered these 

discrepancies. In addition, some flap 

support joints were completely dry due 

to blocked grease paths, and many pins 

were seized in the fittings. Inadequate 

lubrication and the use of clay-based 

lubricants can accelerate pin wear. The 

pins are made of titanium and coated 

with D-gun coating for wear resistance. 

The wear characteristics of titanium 

pins are unknown, so if the wear 

progresses through the D-gun coating, 

the pins could eventually crack and 

then fracture. Moreover, undetected 

wear of the joint bushings results in 

freeplay-induced dynamic loading of 

the pin that is in excess of design loads. 

Wear and corrosion at the flap support 

joints, if not corrected, could result in 

loss of the trailing edge flap and 

possible loss of control of the airplane. 

Relevant Service Information 

We have reviewed Boeing Service 

Bulletin 777–27A0066, Revision 1, 

dated May 18, 2006. The service 

bulletin describes procedures for 

repetitive measurements of the freeplay 

of support joints A, B, C, and D of the 

trailing edge flap supports, numbers 1 

through 3 inclusive and 6 through 8 

inclusive; and of joint B of the trailing 

edge flap supports, numbers 4 and 5. 

The service bulletin also describes 

procedures for disassembling any joint 

that exceeds the freeplay limits 

specified in the service bulletin, and 

doing the related investigative and 

corrective actions in the ‘‘support 

teardown inspection.’’ The related 


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Federal Register / Vol. 72, No. 53 / Tuesday, March 20, 2007 / Proposed Rules 13049 

investigative and corrective actions are 

doing a detailed inspection of the joint 

for worn pins, bearings, and bushings, 

and for blocked lubrication paths; doing 

a dye penetrant inspection for cracks of 

pins with an acceptable surface finish; 

and replacing worn or cracked parts and 

unblocking the lubrication path if 

necessary. 

As an option to the support teardown 

inspection, for certain airplanes, the 

service bulletin describes procedures for 

a ‘‘temporary return to service’’

inspection. The temporary return to 

service inspection is similar to the 

support teardown inspection, except 

inspection for wear of the bearings and 

bushings may be accomplished without 

removing the flap from the airplane by 

insuring that joint freeplay is limited to 

temporarily acceptable levels when 

combined with frequent repetitive 

freeplay inspections. Doing the 

temporary return to service inspection 

extends the compliance time before the 

service bulletin specifies the support 

teardown inspection should be done. 

The service bulletin notes that certain 

pins identified during the support 

teardown inspection or temporary 

return to service inspection are 

acceptable for continued, time-limited 

use if the wear is within certain limits 

specified in the service bulletin. 

The service bulletin also describes 

procedures for repetitive lubrications of 

certain joints of the trailing edge flap 

supports, using Boeing Material 

Standard (BMS) 3–33 grease. The 

service bulletin specifies that part of 

this lubrication is verifying that grease 

emerges from the interface common to 

the pin outer diameter. If grease does 

not emerge, the service bulletin 

describes procedures for doing the 

following related investigative and 

corrective actions: 

• Removing the pin and doing the 

detailed and dye penetrant inspection 

procedures described in the support 

teardown inspection, and replacing 

excessively worn or cracked parts if 

necessary; 

• Inspecting for a blocked lubrication 

path, and clearing it if necessary; and 

• Doing a detailed inspection for wear 

of the interfacing bearings and bushings 

and replacing them if necessary. 

The service bulletin also refers to 

Boeing Alert Service Bulletin 777–

27A0071, Revision 1, dated October 16, 

2006 (described below), which 

eliminates the need for the repetitive 

measurements and lubrications of 

certain trailing edge flap supports after 

accomplishing the specified actions. 

We have also reviewed Boeing Alert 

Service Bulletin 777–27A0071, Revision 

1, dated October 16, 2006. The service 

bulletin describes procedures for 

modifying certain components of the 

trailing edge flap supports. The 

modification includes replacing the 

pins, ball sets, and bushings on the 

joints of the trailing edge flap at support 

numbers 1 through 8 inclusive, with 

new, improved components; doing a 

detailed inspection of the components 

that interface with the flap support pins 

for discrepancies (corrosion, damage, or 

excessive wear); doing a general visual 

inspection of those components for any 

blocked lubrication paths; and doing 

corrective actions if necessary. If any 

discrepancies are found, the corrective 

actions include replacing the 

components and clearing any blocked 

lubrication paths. The service bulletin 

also describes procedures for revising 

the maintenance practices of the Boeing 

777 Maintenance Planning Data (MPD) 

Document to update certain lubrication 

and inspection intervals. Accomplishing 

these actions extends the intervals for 

the repetitive measurement of certain 

trailing edge flap supports specified in 

Boeing Service Bulletin 777–27A0066, 

Revision 1. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to exist or 

develop on other airplanes of this same 

type design. For this reason, we are 

proposing this AD, which would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between the Proposed AD 

and the Service Bulletins.’’

Differences Between the Proposed AD 

and the Service Bulletins 

Note (b) in Table 1 of Paragraph 1.E. 

‘‘Compliance’’ of Boeing Service 

Bulletin 777–27A0066, Revision 1, 

recommends repeating the freeplay 

measurement every 6,000 flight cycles if 

the joints can be proven to have been 

lubricated with only BMS 3–33 grease 

every 1,000 flight cycles or every 240 

days, whichever occurs first, after the 

airplane delivery or the last support 

teardown inspection. However, this 

proposed AD would require repeating 

the freeplay measurement under those 

conditions at intervals not to exceed 

6,000 flight cycles, as specified in the 

service bulletin, but would add a 

compliance time of 120 months 

(whichever occurs first). 

Note (c) in Table 1 of Paragraph 1.E. 

‘‘Compliance’’ of Boeing Service 

Bulletin 777–27A0066, Revision 1, 

specifies that freeplay levels greater 

than 0.020 inch are not recommended 

later than 30 months after release of the 

service bulletin. This proposed AD 

would require the initial measurement 

of the freeplay, for airplanes that have 

accumulated 6,000 total flight cycles or 

more on or before the effective date of 

this AD or on which a teardown 

inspection has not been accomplished 

before the effective date of this AD; at 

the earlier of the following compliance 

times. 

• Prior to the accumulation of 10,000 

total flight cycles, or within 9 months 

after the effective date of this AD, 

whichever occurs later. 

• Within 30 months after the effective 

date of this AD. 

Boeing Alert Service Bulletin 777–

27A0071 specifies revising the 

maintenance practices for performing 

periodic inspections and maintenance 

of the support joints of the trailing edge 

flap for the maintenance inspection 

program of the Boeing 777 MPD 

Document by doing the actions 

specified in Part 7 of the 

Accomplishment Instructions of the 

service bulletin. However, this proposed 

AD would mandate only the 

maintenance actions specified in 

paragraphs 1 and 3 of Part 7 of the 

service bulletin. Parts 3, 4, and 6 of the 

service bulletin include optional actions 

for certain structure in order to increase 

the interval of the repetitive freeplay 

measurement. 

These differences have been 

coordinated with Boeing. 

Costs of Compliance 

There are about 546 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD. 


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13050 Federal Register / Vol. 72, No. 53 / Tuesday, March 20, 2007 / Proposed Rules 

ESTIMATED COSTS

Action Work 

hours 

Average 

labor rate 

per hour 

Parts cost Cost per airplane 

Number 

of U.S.- 

registered 

airplanes 

Fleet cost 

Freeplay measurement, per cycle .......... 28 $80 $0 $2,240, per cycle ....................... 145 $324,800, per cycle. 

Lubrication, per cycle .............................. 2 80 0 $160, per cycle .......................... 145 $23,200 per cycle. 

Modification for flap support No. 3 and 6 135 80 58,521 $69,321 ...................................... 145 $10,051,545. 

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 have 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 that the 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); and 

3. 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. See the ADDRESSES section 

for a location to examine the regulatory 

evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

Boeing: Docket No. FAA–2007–27619; 

Directorate Identifier 2005–NM–164–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by May 4, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 777–

200, –200LR, –300, and –300ER series 

airplanes, certificated in any category; as 

identified in Boeing Service Bulletin 777–

27A0066, Revision 1, dated May 18, 2006. 

Unsafe Condition 

(d) This AD results from reports of 

excessive wear of the pins, bushings, and 

bearings, and corrosion at the joints of the 

outboard trailing edge flap supports. We are 

issuing this AD to prevent wear and 

corrosion at the flap support joints, which 

could result in loss of the trailing edge flap 

and possible loss of control of the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Initial Freeplay Measurement 

(f) At the applicable time in paragraph 

(f)(1) or (f)(2) of this AD: Measure the 

freeplay of support joints A, B, C, and D of 

the trailing edge flap supports, numbers 1 

through 3 inclusive and 6 through 8 

inclusive, and of joint B of the trailing edge 

flap supports, numbers 4 and 5; in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 777–

27A0066, Revision 1, dated May 18, 2006. 

(1) For airplanes that have accumulated 

6,000 total flight cycles or more on or before 

the effective date of this AD or on which a 

teardown inspection has not been 

accomplished before the effective date of this 

AD: At the earlier of the times in paragraph 

(f)(1)(i) or (f)(1)(ii) of this AD. 

(i) Prior to the accumulation of 10,000 total 

flight cycles, or within 9 months after the 

effective date of this AD, whichever occurs 

later. 

(ii) Within 30 months after the effective 

date of this AD. 

(2) For airplanes that have accumulated 

fewer than 6,000 total flight cycles on or 

before the effective date of this AD: At the 

later of the times in paragraph (f)(2)(i) or 

(f)(2)(ii) of this AD. 

(i) Prior to the accumulation of 6,000 total 

flight cycles, or within 120 months after the 

date of issuance of the original standard 

airworthiness certificate or the date of 

issuance of the original export certificate of 

airworthiness, whichever occurs first. 

(ii) Within 30 months after the effective 

date of this AD. 

Repetitive Intervals if the Freeplay 

Measurement Is Less Than 0.020 Inch 

(g) If, during any freeplay measurement 

required by paragraph (f), (g), or (h) of this 

AD, the freeplay measurement is less than 

0.020 inch: Repeat the freeplay measurement 

required by paragraph (f) of this AD at the 

applicable interval in paragraph (g)(1) or 

(g)(2) of this AD. Accomplishing the actions 

specified in paragraph (j) or (k) of this AD, 

as applicable, extends the intervals for the 

repetitive measurements for the associated 

flap support only. 

(1) At intervals not to exceed 1,000 flight 

cycles. 

(2) At intervals not to exceed 6,000 flight 

cycles or 120 months, whichever occurs first, 

if a review of airplane maintenance records 

can conclusively determine that the joints 

have been lubricated with only BMS 3–33 

grease at the earlier of intervals not to exceed 

1,000 flight cycles or 240 days since the last 

support teardown inspection, or since the 

date of issuance of the original standard 

airworthiness certificate or the date of 

issuance of the original export certificate of 

airworthiness. 


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Federal Register / Vol. 72, No. 53 / Tuesday, March 20, 2007 / Proposed Rules 13051 

Related Investigative and Corrective 

Actions, and Repetitive Intervals if the 

Freeplay Measurement Is 0.020 Inch or 

Greater 

(h) If, during any freeplay measurement 

required by paragraph (f), (g), or (h) of this 

AD, the freeplay measurement is 0.020 inch 

or greater: Do the applicable action in 

paragraph (h)(1), (h)(2), or (h)(3) of this AD. 

Accomplishing the actions specified in 

paragraph (j) or (k) of this AD, as applicable, 

extends the intervals for repetitive 

measurements for the associated flap support 

only. Do all actions in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–27A0066, Revision 1, 

dated May 18, 2006, and note (e) of Table 1 

in paragraph 1.E., ‘‘Compliance.’’

(1) For airplanes that have accumulated 

6,000 total flight cycles or more as of the 

effective date of this AD, and for which the 

freeplay measurement is 0.020 inch to 0.100 

inch inclusive: Repeat the freeplay 

measurement required by paragraph (f) of 

this AD thereafter at intervals not to exceed 

500 flight cycles until the support teardown 

inspection in paragraph (h)(1)(i) or (h)(1)(ii) 

of this AD is done. 

(i) Within 12 months after the first freeplay 

measurement of 0.020 inch to 0.100 inch 

inclusive, do the applicable related 

investigative and corrective actions specified 

in the service bulletin as the ‘‘Support 

Teardown Inspection,’’ and repeat the 

freeplay measurement required by paragraph 

(f) of this AD thereafter at intervals not to 

exceed 6,000 flight cycles or 120 months, 

whichever occurs first. 

(ii) Before further flight after the first 

freeplay measurement of 0.020 inch to 0.100 

inch inclusive, do the applicable related 

investigative and corrective actions specified 

in the service bulletin as the ‘‘Temporary 

Return to Service Inspection’’ and, within 24 

months after the first freeplay measurement 

of 0.020 inch to 0.100 inch inclusive, do the 

applicable related investigative and 

corrective actions specified in the service 

bulletin as the ‘‘Support Teardown 

Inspection.’’ Repeat the freeplay 

measurement required by paragraph (f) of 

this AD thereafter at intervals not to exceed 

6,000 flight cycles, or 120 months, whichever 

occurs first. 

(2) For airplanes that have accumulated 

6,000 total flight cycles or more as of the 

effective date of this AD, and the freeplay 

measurement is greater than 0.100 inch: Do 

the action in paragraph (h)(2)(i) or (h)(2)(ii) 

of this AD. 

(i) Before further flight after the first 

freeplay measurement of greater than 0.100 

inch, do the applicable related investigative 

and corrective actions specified in the service 

bulletin as the ‘‘Support Teardown 

Inspection.’’ Repeat the freeplay 

measurement required by paragraph (f) of 

this AD thereafter at intervals not to exceed 

6,000 flight cycles or 120 months, whichever 

occurs first. 

(ii) Before further flight after the first 

freeplay measurement of greater than 0.100 

inch, do applicable related investigative and 

corrective actions in the ‘‘Temporary Return 

to Service Inspection,’’ and within 6 months 

after the first freeplay measurement of greater 

than 0.100 inch, do the applicable related 

investigative and corrective actions in the 

‘‘Support Teardown Inspection.’’ Repeat the 

freeplay measurement required by paragraph 

(f) of this AD thereafter at intervals not to 

exceed 6,000 flight cycles or 120 months, 

whichever occurs first. 

(3) For airplanes that have accumulated 

fewer than 6,000 total flight cycles as of the 

effective date of this AD: Before further flight 

after the first freeplay measurement of 0.020 

inch or greater, do the related investigative 

and corrective actions specified in the service 

bulletin as the ‘‘Support Teardown 

Inspection.’’ Repeat the freeplay 

measurement required by paragraph (f) of 

this AD thereafter at intervals not to exceed 

6,000 flight cycles or 120 months, whichever 

occurs first. 

Repetitive Lubrications 

(i) Within 12 months after the effective 

date of this AD: Lubricate the joints of the 

trailing edge flap supports using BMS 3–33 

grease. Repeat the lubrication thereafter at 

intervals not to exceed 1,000 flight cycles, or 

240 days, whichever occurs first. Do all 

actions in accordance with the 

Accomplishment Instructions, and note (d) of 

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

Boeing Service Bulletin 777–27A0066, 

Revision 1, dated May 18, 2006. 

Modification/Repetitive Freeplay 

Measurements 

(j) Before the accumulation of 23,000 total 

flight cycles or within 24 months after the 

effective date of this AD, whichever is later: 

Replace the pins, ball sets, and bushings on 

the joints of the trailing edge flap at support 

numbers 3 and 6 with new, improved 

components by doing all the applicable 

actions, including all applicable corrective 

actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–27A0071, Revision 1, 

dated October 16, 2006. Before further flight 

after doing the actions, do a detailed 

inspection of the components that interface 

with the flap support pins for discrepancies 

(corrosion, damage, or excessive wear), and 

a general visual inspection for any blocked 

lubrication paths; and do all applicable 

corrective actions. Repeat the freeplay 

measurements for the associated flap support 

at intervals not to exceed 16,000 flight cycles 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

777–27A0071, Revision 1, dated October 16, 

2006. Accomplishing the actions in this 

paragraph constitutes terminating action for 

the actions specified in paragraphs (f), (g), 

(h), and (i) of this AD, for the associated 

trailing edge flap support only. 

Optional Modification 

(k) Accomplishing the actions specified in 

paragraph (j) of this AD at support numbers 

1, 2, 4, 5, 7, and 8, extends the intervals for 

the repetitive measurements required by 

paragraph (g) of this AD for the associated 

flap support only. 

Revise Maintenance Planning Data (MPD) 

Document 

(l) Within 12 months after the effective 

date of this AD: Revise the maintenance 

practices for performing periodic inspections 

and maintenance of the support joints of the 

trailing edge flap for the maintenance 

inspection program of the Boeing 777 MPD 

Document by doing the actions specified in 

paragraphs 1 and 3 only of Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–27A0071, Revision 1, 

dated October 16, 2006. 

Actions Accomplished Previously 

(m) Actions done before the effective date 

of this AD in accordance with Boeing Alert 

Service Bulletin 777–27A0066, dated July 28, 

2005, are acceptable for compliance with 

paragraphs (f), (g), (h), and (i) of this AD, as 

applicable. Actions done before the effective 

date of this AD in accordance with Boeing 

Alert Service Bulletin 777–27A0071, dated 

March 30, 2006, are acceptable for 

compliance with paragraphs (j), (k), and (l) of 

this AD, as applicable. 

Alternative Methods of Compliance 

(AMOCs) 

(n)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards 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 an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who 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. 

Issued in Renton, Washington, on March 9, 

2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–5013 Filed 3–19–07; 8:45 am] 

BILLING CODE 4910–13–P 

FEDERAL TRADE COMMISSION 

16 CFR Part 255 

Guides Concerning the Use of 

Endorsements and Testimonials in 

Advertising 

AGENCY: Federal Trade Commission. 

ACTION: Extension of deadline for 

submission of comments. 

SUMMARY: The Federal Trade 

Commission (‘‘FTC’’ or ‘‘Commission’’) 

is extending until June 18, 2007 the 

deadline for filing comments on the 

Guides and on two consumer surveys 

commissioned by the Commission 


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