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

37332 

Vol. 77, No. 120 

Thursday, June 21, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0724; Directorate 

Identifier 2010–NM–181–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 

757–200, –200PF, and –200CB series 

airplanes powered by Rolls-Royce 

engines. That NPRM proposed to 

supersede an existing AD that requires 

repetitive inspections of the shim 

installation between the drag brace 

fitting vertical flange and bulkhead, and 

repair if necessary; for certain airplanes, 

an inspection for cracking of the four 

critical fastener holes in the horizontal 

flange, and repair if necessary; and, for 

airplanes without conclusive records of 

previous inspections, performing the 

existing actions. That NPRM proposed 

to reduce the repetitive inspection 

interval, add repetitive detailed 

inspections for cracking of the 

bulkhead, and repair if necessary; 

extend the repetitive intervals for 

certain airplanes by also doing 

repetitive ultrasonic inspections for 

cracking of the bulkhead, and repair if 

necessary; and an option for the high 

frequency eddy current inspection for 

cracking of the critical fastener holes, 

and repair if necessary. That NPRM was 

prompted by reports of loose fasteners 

and cracks at the joint common to the 

aft torque bulkhead and strut-todiagonal brace fitting, and one report of 

such damage occurring less than 3,000 

flight cycles after the last inspection. 

This action revises that NPRM by 

adding a terminating action for certain 

repetitive inspections. We are proposing 

the supplemental NPRM to detect and 

correct cracks, loose and broken bolts, 

and shim migration in the joint between 

the aft torque bulkhead and the strut-todiagonal brace fitting, which could 

result in damage to the strut and 

consequent separation of the strut and 

engine from the airplane. Since these 

actions impose an additional burden 

over that proposed in the 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 

the supplemental NPRM by August 6, 

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, WA 98124–2207; 

phone: 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 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: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, Seattle 

Aircraft Certification Office (ACO), 

FAA, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6440; fax: 425–917–6590; email: 

Nancy.Marsh@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–2011–0724; Directorate Identifier 

2010–NM–181–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We issued an NPRM to amend 14 CFR 

part 39 to supersede AD 2008–05–10, 

Amendment 39–15404 (73 FR 11347, 

March 3, 2008), to include an AD 

applies to certain The Boeing Company 

Model 757–200, –200PF, and –200CB 

series airplanes powered by Rolls-Royce 

engines. That NPRM was published in 

the Federal Register on August 24, 2011 

(76 FR 52901). That NPRM proposed to 

continue to repetitive inspections of the 

shim installation between the drag brace 

fitting vertical flange and bulkhead, and 

repair if necessary; for certain airplanes, 

an inspection for cracking of the four 

critical fastener holes in the horizontal 

flange, and repair if necessary; and, for 

airplanes without conclusive records of 

previous inspections, performing the 

existing actions. Additionally, the 

existing AD requires that the existing 


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action be performed on airplanes 

without conclusive records of previous 

inspections. That NPRM proposed to 

reduce the repetitive inspection 

interval, and add repetitive detailed 

inspections for cracking of the 

bulkhead, and repair if necessary. That 

NPRM proposed an option, for certain 

airplanes, to extend the repetitive 

intervals by also doing repetitive 

ultrasonic inspections for cracking of 

the bulkhead, and repair if necessary; 

and proposed an option to the high 

frequency eddy current inspection for 

cracking of the critical fastener holes, 

and repair if necessary. 

Actions Since Previous NPRM (76 FR 

52901, August 24, 2011) Was Issued 

Since we issued the previous NPRM 

(76 FR 52901, August 24, 2011), new 

service information has been issued that 

specifies additional actions that are 

necessary to address the identified 

unsafe condition, and also describes a 

terminating action for the repetitive 

inspections on certain airplanes. 

Comments 

We gave the public the opportunity to 

comment on the previous NPRM (76 FR 

52901, August 24, 2011). The following 

presents the comments received on the 

NPRM and the FAA’s response to each 

comment. 

Agreement With the Previous NPRM 

(76 FR 52901, August 24, 2011) 

Continental Airlines (Continental) 

stated it concurs in general with 

previous NPRM (76 FR 52901, August 

24, 2011) to mandate Boeing Alert 

Service Bulletin 757–54A0047, Revision 

4, dated June 24, 2010, inspections. 

Request To Reference Revised Service 

Information 

Continental, UPS, European Air 

Transport Leipzig GmbH (EATL), and 

FedEx requested that the previous 

NPRM (76 FR 52901, August 24, 2011) 

be changed to include Boeing Alert 

Service Bulletin 757–54A0047, Revision 

5, dated June 9, 2011. The commenters 

stated this revised service information 

includes a terminating action for the 

repetitive inspections. 

We agree because Boeing Alert 

Service Bulletin 757–54A0047, Revision 

5, dated June 9, 2011, includes 

terminating action to address the unsafe 

condition. Boeing Alert Service Bulletin 

757–54A0047, Revision 5, dated June 9, 

2011, describes procedures for certain 

airplanes for replacing the horizontal 

and vertical flange fasteners in the strutto-diagonal brace fitting on the number 

1 and number 2 struts with new 

fasteners, and doing related 

investigative and corrective actions if 

necessary. The related investigative 

action is an eddy current inspection for 

cracking of the critical fastener holes in 

the horizontal and vertical flange. The 

corrective action is contacting Boeing 

for repair instructions and doing the 

repair. We have changed this 

supplemental NPRM to refer to Boeing 

Alert Service Bulletin 757–54A0047, 

Revision 5, dated June 9, 2011, and have 

made the terminating action specified in 

this service information mandatory. We 

have also added paragraph (p) in this 

supplemental NPRM to provide credit 

for actions accomplished before the 

effective date of the AD using Boeing 

Alert Service Bulletin 757–54A0047, 

Revision 4, dated June 24, 2010. 

Request To Include Alternative Method 

of Compliance (AMOC) in Previous 

NPRM (76 FR 52901, August 24, 2011) 

Continental requested a paragraph be 

added to the previous NPRM (76 FR 

52901, August 24, 2011) that approves 

accomplishment of the terminating 

modification specified in Boeing Alert 

Service Bulletin 757–54A0047, Revision 

5, dated June 9, 2011, as an AMOC with 

the actions specified in paragraphs (g), 

(h), (l), (q), and (r) of the previous 

NPRM. The commenter did not provide 

any justification for this request. 

We disagree with adding an AMOC 

provision to the supplemental NPRM. 

As previously stated, we are changing 

the supplemental NPRM to mandate the 

terminating action specified in Boeing 

Alert Service Bulletin 757–54A0047, 

Revision 5, dated June 9, 2011, which 

would terminate the inspections 

specified in paragraphs (g), (h), (j), and 

(m) of the supplemental NPRM for 

Group 1, Configuration 2 airplanes; and 

Group 2 airplanes; as identified in 

Boeing Alert Service Bulletin 757– 

54A0047, Revision 5, dated June 9, 

2011. These supplemental NPRM 

paragraphs are the same paragraphs 

specified by the commenter (paragraphs 

(j) and (m) of the supplemental NPRM 

correspond to paragraphs (l) and (q) in 

the previous NPRM (76 FR 52901, 

August 24, 2011)). The commenter also 

included paragraph (r) of the previous 

NPRM (which is paragraph (n) in the 

supplemental NPRM); however, that 

paragraph is not pertinent since it 

provides the compliance times for 

paragraph (m) in the supplemental 

NPRM. Termination of the inspections 

specified in paragraphs (g), (h), (j), and 

(m) of this supplemental NPRM, 

through accomplishment of the 

modification required by paragraph (o) 

of this supplemental NPRM, has the 

same result as the AMOC requested by 

the commenter, since use of Boeing 

Alert Service Bulletin 757–54A0047, 

Revision 5, dated June 9, 2011, is being 

proposed. We have not changed the 

supplemental NPRM in this regard. 

Request To Add Actions Specified in 

Revised Service Information 

Boeing proposed language for three 

new paragraphs to the previous NPRM 

(76 FR 52901, August 24, 2011), which 

correspond to paragraphs (s), (t), and (u) 

of the previous NPRM, that would 

require certain actions specified in 

Boeing Alert Service Bulletin 757– 

54A0047, Revision 5, dated June 9, 

2011. The actions in Boeing’s proposed 

paragraphs included installation of 

larger diameter fasteners, as specified in 

Boeing Alert Service Bulletin 757– 

54A0047, Revision 5, dated June 9, 

2011, ‘‘within 9,000 flight cycles or 54 

months, whichever is earlier, after the 

effective date of the AD;’’ crack repair 

instructions for cracking found during 

the fastener modification; and 

termination of inspections required in 

paragraphs (h), (l)(2), and (q) of the 

previous NPRM. 

We partially agree. We agree to refer 

to Boeing Alert Service Bulletin 757– 

54A0047, Revision 5, dated June 9, 

2011, because it provides additional 

actions and a modification to address 

the unsafe condition for certain 

airplanes. We disagree with adding the 

specific paragraphs proposed by Boeing 

because we are issuing a supplemental 

NPRM that proposes to mandate Boeing 

Alert Service Bulletin 757–54A0047, 

Revision 5, dated June 9, 2011. 

Therefore, the paragraphs proposed by 

Boeing that specify installing larger 

diameter fasteners and the compliance 

time are unnecessary. We have not 

changed the supplemental NPRM in this 

regard. 

Boeing also proposed a paragraph that 

defines the terminating action for the 

repetitive inspections required by 

paragraphs (h), (l)(2), and (q) of the 

previous NPRM (76 FR 52901, August 

24, 2011). Part of the commenter’s 

proposed terminating action paragraph 

for Group 1, Configuration 1 airplanes; 

and Group 2 airplanes; is unnecessary. 

Boeing Alert Service Bulletin 757– 

54A0047, Revision 5, dated June 9, 

2011, specified in the supplemental 

NPRM, already includes this 

information. Additionally, the 

commenter’s proposed terminating 

action paragraph stated that 

modification of the strut, in accordance 

with Boeing Alert Service Bulletin 757– 

54A0047, Revision 5, dated June 9, 

2011, terminates the repetitive 

inspections of paragraphs (h), (l)(2), and 

(q) of the previous NPRM for Group 1, 

Configuration 1 airplanes. 


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We disagree with changing the 

supplemental NPRM to include this 

information as it is redundant to the 

information included in Boeing Alert 

Service Bulletin 757–54A0047, Revision 

5, dated June 9, 2011. This service 

information defines Group 1, 

Configuration 1 airplanes, as airplanes 

that have not accomplished the 

modifiction described in Boeing Service 

Bulletin 757–54–0035, thus the 

signficance of the strut modification 

accomplishment is clearly specified. We 

have not changed the supplemental 

NPRM in this regard. 

Request To Add an AMOC Into the 

Previous NPRM (76 FR 52901, August 

24, 2011) 

Boeing requested we add a paragraph 

to the previous NPRM (76 FR 52901, 

August 24, 2011) stating that 

inspections and repairs done in 

accordance with Boeing Alert Service 

Bulletin 757–54A0047, Revision 5, 

dated June 9, 2011, are an AMOC for the 

corresponding requirements of the AD. 

Boeing stated that the inspections and 

repairs for Boeing Alert Service Bulletin 

757–54A0047, Revision 5, dated June 9, 

2011, are equivalent to the 

corresponding inspections and repairs 

specified in Boeing Alert Service 

Bulletin 757–54A0047, Revision 4, 

dated June 24, 2010, and since Boeing 

Alert Service Bulletin 757–54A0047, 

Revision 5, dated June 9, 2011, is 

already published and in use by the 

operators, this would eliminate the need 

for a separate global AMOC for Boeing 

Alert Service Bulletin 757–54A0047, 

Revision 5, dated June 9, 2011, relative 

to this AD. 

We partially agree. The previous 

NPRM (76 FR 52901, August 24, 2011) 

did reference Boeing Alert Service 

Bulletin 757–54A0047, Revision 4, 

dated June 24, 2010. We agree that the 

actions specified in Boeing Alert Service 

Bulletin 757–54A0047, Revision 5, 

dated June 9, 2011, are equivalent to the 

corresponding actions specified in 

Boeing Alert Service Bulletin 757– 

54A0047, Revision 4, dated June 24, 

2010. However, as stated previously, the 

supplemental NPRM references Boeing 

Alert Service Bulletin 757–54A0047, 

Revision 5, dated June 9, 2011, 

eliminating the need for an AMOC. We 

have not changed the supplemental 

NPRM in this regard. 

Explanation of Additional Changes 

Made to This Supplemental NPRM 

We have revised certain headings 

throughout this supplemental NPRM. 

The credit for previous 

accomplishment of the actions required 

by AD 2008–05–10, Amendment 39– 

15404 (73 FR 11347, March 3, 2008), 

specified in paragraphs (n) and (o) of the 

previous NPRM (76 FR 52901, August 

24, 2011), has been moved to paragraph 

(p) of the supplemental NPRM. 

We have revised the heading and 

wording for paragraphs (n) and (o) of 

this AD. This change does not affect the 

intent of those paragraphs. 

We revised paragraph (l) of this 

supplemental NPRM to refer to 

paragraphs (b) and (d) of AD 2004–12– 

07, Amendment 39–13666 (69 FR 

33561, June 16, 2004), instead of 

paragraphs (b) and (c) of AD 2004–12– 

07, because paragraph (d) of AD 2004– 

12–07 contains the inspection of the 

fastener holes and inspection of the 

fasteners common to the lower spar 

fitting and strut aft bulkhead. Paragraph 

(c) of AD 2004–12–07 is a preliminary 

inspection of the middle gusset of the 

inboard side load fitting. We also 

revised paragraph (p) of this 

supplemental NPRM to reference 

paragraph (d) of AD 2004–12–07, 

instead of paragraph (c) of AD 2004–12– 

07. 

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 the same type 

design. Certain changes described above 

expand the scope of the original NPRM 

(76 FR 52901, August 24, 2011). 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 

retain all the requirements of AD 2008– 

05–10, Amendment 39–15404 (73 FR 

11347, March 3, 2008); reduce the 

repetitive inspection interval for 

cracking, and add repetitive detailed 

inspections for cracking of the 

bulkhead, and repair if necessary. This 

supplemental NPRM would also, for 

certain airplanes, add an option to 

extend the repetitive intervals by also 

doing repetitive ultrasonic inspections 

for cracking of the bulkhead, and repair 

if necessary; and add an option to the 

high frequency eddy current inspection 

for cracking of the critical fastener 

holes, and repair if necessary. This 

supplemental NPRM would also require 

replacing certain horizontal and vertical 

flange fasteners in the strut-to-diagonal 

brace fittings and accomplishing the 

actions specified in the service 

information described previously, 

except as discussed under ‘‘Differences 

Between the Supplemental NPRM and 

the Service Information.’’ 

Differences Between the Supplemental 

NPRM and the Service Information 

Boeing Alert Service Bulletin 757– 

54A0047, Revision 5, dated June 9, 

2011, specifies to contact the 

manufacturer for instructions on how to 

repair certain conditions, but this 

supplemental NPRM would require 

repairing those conditions in one of the 

following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Accomplishment of the actions 

required in paragraph (o) of this 

supplemental NPRM would terminate 

the inspection requirements of 

paragraphs (g), (h), (j), and (m) of this 

supplemental NPRM for Group 1, 

Configuration 2 airplanes; and Group 2 

airplanes; as identified in Boeing Alert 

Service Bulletin 757–54A0047, Revision 

5, dated June 9, 2011. 

Costs of Compliance 

We estimate that this proposed AD 

affects 309 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 

Part I Inspection on fasteners and shims— 

vertical flange [retained actions from AD 2008– 

05–10, Amendment 39–15404 (73 FR 11347, 

March 3, 2008)] 

28 work-hours × $85 per 

hour = $2,380 per inspection cycle 

$0 $2,380 per inspection 

cycle 

$735,420 per inspection 

cycle 


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ESTIMATED COSTS—Continued 

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Part II Inspection on fasteners—horizontal flange 

[retained actions from AD 2008–05–10, 

Amendment 39–15404 (73 FR 11347, March 

3, 2008)] 

6 work-hours × $85 per 

hour = $510 per inspection cycle 

0 $510 per inspection 

cycle 

$157,590 per inspection 

cycle. 

Part IV inspection on critical fasteners—horizontal flange [retained actions from AD 2008– 

05–10, Amendment 39–15404 (73 FR 11347, 

March 3, 2008)] 

6 work-hours × $85 per 

hour = $510 per inspection cycle 

0 $510 per inspection 

cycle 

$157,590 per inspection 

cycle. 

Part II Additional inspection actions on fasteners—horizontal flange [new proposed action] 10 work-hours × $85 per 

hour = $850 per inspection cycle 

0 $850 per inspection 

cycle 

$262,650 per inspection 

cycle. 

Part IV inspection on critical fasteners—horizontal flange [new proposed action] 8 to 22 work-hours × 

$85 per hour = $680 

to $1,870 per inspection cycle 

0 $680 to $1,870 per inspection cycle $210,120 to $577,830 

per inspection cycle. 

Part V fastener replacement flange [new proposed action] Up to 37 work-hours × 

$85 per hour = 

$3,145 per strut 

750 Up to $3,895 per strut Up to $1,203,555 per 

strut. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

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 

removing airworthiness directive (AD) 

2008–05–10, Amendment 39–15404 (73 

FR 11347, March 3, 2008), and adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2011–0724; Directorate Identifier 2010– 

NM–181–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by August 6, 2012. 

(b) Affected ADs 

This AD supersedes AD 2008–05–10, 

Amendment 39–15404 (73 FR 11347, March 

3, 2008). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 757–200, –200PF, and –200CB series 

airplanes; certificated in any category; line 

numbers 1 through 1048 inclusive; powered 

by Rolls-Royce engines. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 54, Nacelles/Pylons. 

(e) Unsafe Condition 

This AD was prompted by reports of loose 

fasteners and cracks at the joint common to 

the aft torque bulkhead and strut-to-diagonal 

brace fitting, and one report of such damage 

occurring less than 3,000 flight cycles after 

the last inspection. We are issuing this AD 

to detect and correct cracks, loose and broken 

bolts, and shim migration in the joint 

between the aft torque bulkhead and the 

strut-to-diagonal brace fitting, which could 

result in damage to the strut and consequent 

separation of the strut and engine from the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained One-Time Inspection and 

Repair With Optional Inspection Method, 

With Reduced Repetitive Intervals and New 

Optional Inspection Method 

This paragraph restates the one-time 

inspection and repair with optional 

inspection method required by paragraph (g) 

of AD 2008–05–10, Amendment 39–15404 

(73 FR 11347, March 3, 2008), with reduced 

repetitive intervals, and a new optional 

inspection method, with revised service 

information. For airplanes identified in 

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

Within 90 days after August 24, 2007 (the 

effective date of AD 2007–16–13, 

Amendment 39–15152 (72 FR 44753, August 

9, 2007)), do a high frequency eddy current 

(HFEC) inspection for cracking of the four 

critical fastener holes in the horizontal flange 

and, before further flight, do all applicable 


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repairs, in accordance with Part IV of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 757–54A0047, Revision 3, 

dated June 27, 2007; Boeing Alert Service 

Bulletin 757–54A0047, Revision 4, dated 

June 24, 2010; or Boeing Alert Service 

Bulletin 757–54A0047, Revision 5, dated 

June 9, 2011; except as required by paragraph 

(i)(3) of this AD. As of the effective date of 

this AD, only Boeing Alert Service Bulletin 

757–54A0047, Revision 5, dated June 9, 

2011, may be used to accomplish the actions 

required by this paragraph. Doing an 

ultrasonic inspection for cracking of the 

fasteners, in accordance with Part IV of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 757–54A0047, Revision 4, 

dated June 24, 2010; or Boeing Alert Service 

Bulletin 757–54A0047, Revision 5, dated 

June 9, 2011; is an acceptable method for 

compliance with the HFEC inspection 

requirement of this paragraph. 

(1) Airplanes on which findings on the 

horizontal or vertical fasteners or the shims 

led to a rejection of any fastener during the 

actions specified in Boeing Alert Service 

Bulletin 757–54A0047, dated November 13, 

2003; or Boeing Service Bulletin 757– 

54A0047, Revision 1, dated March 24, 2005. 

(2) Airplanes that had equivalent findings 

prior to Boeing Alert Service Bulletin 757– 

54A0047, dated November 13, 2003, except 

for findings on airplanes identified as Group 

1, Configuration 2, in Boeing Alert Service 

Bulletin 757–54A0047, Revision 3, dated 

June 27, 2007, that were prior to the 

incorporation of Boeing Service Bulletin 

757–54–0035. 

(h) Retained Repetitive Inspection and 

Repair, With Reduced Interval 

This paragraph restates the repetitive 

inspection and repair required by paragraph 

(h) of AD 2008–05–10, Amendment 39– 

15404 (73 FR 11347, March 3, 2008), with 

reduced repetitive intervals and revised 

service information. At the applicable initial 

times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 757–54A0047, Revision 3, dated 

June 27, 2007, except as required by 

paragraphs (i)(1) and (i)(2) of this AD: Do the 

inspections specified in paragraphs (h)(1), 

(h)(2), and (h)(3) of this AD, and before 

further flight, do all the applicable related 

investigative actions and repairs, by doing all 

the actions specified in Parts I and II of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 757–54A0047, Revision 3, 

dated June 27, 2007; or by doing all the 

actions in Part I and in Step 2 of Part II of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 757–54A0047 Revision 

4, dated June 24, 2010, or Boeing Alert 

Service Bulletin 757–54A0047, Revision 5, 

dated June 9, 2011, except as required by 

paragraph (i)(3) of this AD. As of the effective 

date of this AD, only Boeing Alert Service 

Bulletin 757–54A0047, Revision 5, dated 

June 9, 2011, may be used to accomplish the 

actions required by this paragraph. Repeat 

the inspections required by this paragraph at 

the times specified in paragraph (h)(4) of this 

AD. 

(1) Do detailed inspections of the shim 

installations between the vertical flange and 

bulkhead to determine if there are signs of 

movement. 

(2) Do detailed inspections of the four 

fasteners in the vertical flange to determine 

if there are signs of movement or if there are 

gaps under the head or collar. 

(3) Do detailed inspections of the fasteners 

that hold the strut to the horizontal flange of 

the strut-to-diagonal brace fitting to 

determine if there are signs of movement or 

if there are gaps under the head or collar. 

(4) Repeat the inspections required by 

paragraph (h) of this AD at the earlier of the 

times specified in paragraphs (h)(4)(i) and 

(h)(4)(ii) of this AD. Thereafter, repeat the 

inspections at intervals not to exceed the 

applicable intervals specified in paragraph 

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

Bulletin 757–54A0047, Revision 5, dated 

June 9, 2011. 

(i) At intervals not to exceed the applicable 

intervals specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 757–54A0047, Revision 3, dated 

June 27, 2007. 

(ii) At intervals not to exceed the 

applicable intervals specified in paragraph 

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

Bulletin 757–54A0047, Revision 5, dated 

June 9, 2011; or within 90 days after the 

effective date of this AD; whichever occurs 

later. 

(i) Retained Exceptions to Alert Service 

Bulletin Procedures 

This paragraph restates the exceptions to 

alert service bulletin procedures required by 

paragraphs (i), (j), and (k) of AD 2008–05–10, 

Amendment 39–15404 (73 FR 11347, March 

3, 2008), with revised service information. 

(1) Where Boeing Alert Service Bulletin 

757–54A0047, Revision 3, dated June 27, 

2007, specifies a compliance time relative to 

‘‘the date on this service bulletin,’’ this AD 

requires compliance within the 

corresponding specified time relative to the 

effective date of AD 2007–16–13, 

Amendment 39–15152 (72 FR 44753, August 

9, 2007). 

(2) Where Boeing Alert Service Bulletin 

757–54A0047, Revision 3, dated June 27, 

2007, specifies a compliance time relative to 

the ‘‘date of issuance of airworthiness 

certificate,’’ this AD requires compliance 

within the corresponding time relative to the 

date of issuance of the original standard 

airworthiness certificate or the date of 

issuance of the original export certificate of 

airworthiness. 

(3) If any crack is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 757–54A0047, 

Revision 3, dated June 27, 2007; Boeing Alert 

Service Bulletin 757–54A0047, Revision 4, 

dated June 24, 2010; or Boeing Alert Service 

Bulletin 757–54A0047, Revision 5, dated 

June 9, 2011; specifies to contact Boeing for 

appropriate action: Before further flight, 

repair the crack using a method approved in 

accordance with the procedures specified in 

paragraph (q) of this AD. 

(j) Retained Inspection/Repair for Airplanes 

for Which There Are No Conclusive 

Inspection Records 

This paragraph restates the inspection/ 

repair requirements for airplanes for which 

there are no conclusive inspection records, as 

required by paragraph (l) of AD 2008–05–10, 

Amendment 39–15404 (73 FR 11347, March 

3, 2008), with revised service information. 

For airplanes for which there are no 

conclusive records showing no loose or 

missing fasteners during previous 

inspections done in accordance with the 

requirements of AD 2007–16–13, 

Amendment 39–15152 (72 FR 44753, August 

9, 2007); or AD 2005–12–04, Amendment 39– 

14120 (70 FR 34313 June 14, 2005): Do the 

actions specified in paragraphs (j)(1) and 

(j)(2) of this AD, at the times specified in 

those paragraphs, as applicable. 

(1) Within 90 days after March 18, 2008 

(the effective date of AD 2008–05–10, 

Amendment 39–15404 (73 FR 11347, March 

3, 2008)), do the actions specified in 

paragraph (g) of this AD, except as required 

by paragraph (i)(3) of this AD. 

(2) At the applicable initial times specified 

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

Alert Service Bulletin 757–54A0047, 

Revision 3, dated June 27, 2007, do the 

actions specified in paragraph (h) of this AD, 

except as required by paragraphs (i)(2) and 

(k) of this AD. And, before further flight, do 

all applicable related investigative actions 

and repairs, by doing all the actions specified 

in Parts I and II of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–54A0047, Revision 3, dated June 27, 

2007; or in Part 1 and in Step 2 of Part II of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 757–54A0047 Revision 

4, dated June 24, 2010, or Boeing Alert 

Service Bulletin 757–54A0047, Revision 5, 

dated June 9, 2011, except as required by 

paragraph (i)(3) of this AD. As of the effective 

date of this AD, only Boeing Alert Service 

Bulletin 757–54A0047, Revision 5, dated 

June 9, 2011, may be used to accomplish the 

actions required by this paragraph. Repeat 

the actions specified in paragraph (h) of this 

AD at the times specified in paragraph (h)(4) 

of this AD. 

(k) Retained Exception to Alert Service 

Bulletin Procedures 

This paragraph restates the exception to 

alert service bulletin procedures required by 

paragraph (m) of AD 2008–05–10, 

Amendment 39–15404 (73 FR 11347, March 

3, 2008). Where Boeing Alert Service Bulletin 

757–54A0047, Revision 3, dated June 27, 

2007, specifies a compliance time relative to 

‘‘the date on this service bulletin,’’ this AD 

requires compliance within the 

corresponding specified time relative to the 

effective date of AD 2008–05–10. 

(l) Retained Acceptable Method of 

Compliance With Certain Requirements of 

AD 2004–12–07, Amendment 39–13666 (69 

FR 33561 June 16, 2004) 

This paragraph restates an acceptable 

method of compliance with certain 

requirements of AD 2004–12–07, 

Amendment 39–13666 (69 FR 33561 June 16, 

2004), specified by paragraph (p) of AD 

2008–05–10, Amendment 39–15404 (73 FR 

11347, March 3, 2008). Accomplishing the 

actions specified in paragraphs (g) and (h) of 

this AD terminates the requirements 

specified in paragraphs (b) and (d) of AD 

2004–12–07. 


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Federal Register / Vol. 77, No. 120 / Thursday, June 21, 2012 / Proposed Rules 37337 

(m) New Repetitive Inspections and Repair 

At the applicable initial compliance times 

specified in paragraph (n) of this AD: Do the 

applicable actions specified in paragraph 

(m)(1) or (m)(2) of this AD, in accordance 

with Step 3 of Part II of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–54A0047, Revision 4, dated June 24, 

2010; or Boeing Alert Service Bulletin 757– 

54A0047, Revision 5, dated June 9, 2011. If 

no cracking is found, repeat the inspections 

thereafter at intervals not to exceed the 

applicable intervals specified in paragraph 

1.E., ‘‘Compliance,’’ of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–54A0047, Revision 5, dated June 9, 

2011. If any crack is found during any 

inspection required by this paragraph, before 

further flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (q) of this AD. 

(1) For Group 1, Configuration 1 airplanes 

identified in Boeing Alert Service Bulletin 

757–54A0047, Revision 5, dated June 9, 

2011: Do the actions specified in paragraph 

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

(i) Do a detailed inspection for cracking of 

the bulkhead in the area around the access 

door cutout and around the critical fasteners 

in the horizontal flange. 

(ii) Do a detailed inspection for cracking of 

the bulkhead in the area around the access 

door cutout and around the critical fasteners 

in the horizontal flange, and do an ultrasonic 

inspection for cracking of the bulkhead 

around the fasteners in the horizontal flange. 

Doing the actions in this paragraph extends 

the repetitive intervals of the inspections 

required by paragraph (n) of this AD. 

(2) For Group 1, Configuration 2 airplanes; 

and Group 2 airplanes; identified in Boeing 

Alert Service Bulletin 757–54A0047, 

Revision 5, dated June 9, 2011: Do a detailed 

inspection for cracking of the bulkhead in the 

area around the access door cutout and 

around the critical fasteners in the horizontal 

flange. 

(n) New Compliance Times for Paragraph 

(m) of This AD 

At the applicable times specified in 

paragraphs (n)(1) and (n)(2) of this AD, do the 

actions required by paragraph (m) of this AD. 

(1) For Group 1, Configuration 1 airplanes 

identified in Boeing Alert Service Bulletin 

757–54A0047, Revision 5, dated June 9, 

2011: At the later of the times specified in 

paragraph (n)(1)(i) or (n)(1)(ii) of this AD. 

(i) Within 1,800 flight cycles after 

accomplishing the most recent inspection 

required by paragraph (h) or (j) of this AD. 

(ii) Within 90 days after the effective date 

of this AD. 

(2) For Group 1, Configuration 2 airplanes; 

and Group 2 airplanes; identified in Boeing 

Alert Service Bulletin 757–54A0047, 

Revision 5, dated June 9, 2011: At the later 

of the times specified in paragraph (n)(2)(i) 

or (n)(2)(ii) of this AD. 

(i) Within 3,000 flight cycles after 

accomplishing the most recent inspection 

required by paragraph (h) or (j) of this AD. 

(ii) Within 90 days after the effective date 

of this AD. 

(o) New Terminating Action for Certain 

Airplanes: Fastener Replacement 

For Group 1, Configuration 2 airplanes; 

and Group 2 airplanes; as identified in 

Boeing Alert Service Bulletin 757–54A0047, 

Revision 5, dated June 9, 2011: Within 9,000 

flight cycles or 54 months after the effective 

date of this AD, whichever occurs first, 

replace the horizontal and vertical flange 

fasteners in the strut-to-diagonal brace fitting 

on the number 1 and number 2 struts with 

new fasteners and do all related investigative 

and applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–54A0047, Revision 5, dated June 9, 

2011, except where Boeing Alert Service 

Bulletin 757–54A0047, Revision 5, dated 

June 9, 2011, specifies to contact Boeing for 

repair instructions, before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (q) of this AD. Do all related 

investigative and corrective actions before 

further flight. Accomplishment of the actions 

required in paragraph (o) of this AD 

terminates the inspection requirements of 

paragraphs (g), (h), (j), and (m) of this AD for 

Group 1, Configuration 2 airplanes; and 

Group 2 airplanes; as identified in Boeing 

Alert Service Bulletin 757–54A0047, 

Revision 5, dated June 9, 2011. 

(p) Credit for Previous Actions 

(1) Except for the actions specified in 

paragraphs (j), (m), and (o) of this AD, this 

paragraph provides credit for the actions 

required by paragraphs (g) and (h) of this AD, 

if those actions were done before March 18, 

2008 (the effective date of AD 2008–05–10, 

Amendment 39–15404 (73 FR 11347, March 

3, 2008), using Boeing Service Bulletin 757– 

54A0047, Revision 1, dated March 24, 2005; 

or Boeing Alert Service Bulletin 757– 

54A0047, Revision 2, dated January 31, 2007. 

(2) This paragraph provides credit for the 

initial inspection required by paragraph (h) 

of this AD, if that inspection was done before 

June 29, 2005 (the effective date of AD 2005– 

12–04, Amendment 39–14120 (70 FR 34313, 

June 14, 2005)), using the actions required by 

paragraph (b) or (d), as applicable, of AD 

2004–12–07, Amendment 39–13666 (69 FR 

33561, June 16, 2004). 

(q) 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. 

(4) AMOCs approved previously in 

accordance with AD 2004–12–07, 

Amendment 39–13666 (69 FR 33561, June 

16, 2004), are approved as AMOCs for the 

corresponding provisions of this AD. 

(5) AMOCs approved previously in 

accordance with AD 2005–12–04, 

Amendment 39–14120 (70 FR 34313, June 

14, 2005), are approved as AMOCs for the 

corresponding provisions of this AD. 

(6) AMOCs approved previously in 

accordance with AD 2007–16–13, 

Amendment 39–15152 (72 FR 44753, August 

9, 2007), are approved as AMOCs for the 

corresponding provisions of this AD. 

(7) AMOCs approved previously in 

accordance with AD 2008–05–10, 

Amendment 39–15404 (73 FR 11347, March 

3, 2008), are approved as AMOCs for the 

corresponding provisions of this AD. 

(r) Related Information 

(1) For more information about this AD, 

contact Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, Seattle 

Aircraft Certification Office (ACO), FAA, 

1601 Lind Avenue SW., Renton, Washington 

98057–3356; phone 425–917–6440; fax 425– 

917–6590; email: Nancy.Marsh@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; phone: 

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

5680; 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 June 14, 

2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–15181 Filed 6–20–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0643; Directorate 

Identifier 2011–NM–190–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS