40508 Federal Register / Vol. 82, No. 164 / Friday, August 25, 2017 / Proposed Rules 

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 

certification office, send it to the attention of 

the person identified in paragraph (k)(1) of 

this AD. Information may be emailed to: 9- 

ANM-LAACO-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, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO Branch, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) Except as required by paragraph (h) of 

this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (j)(4)(i) and (j)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. If a step or substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. An AMOC is required for any 

deviations to RC steps, including substeps 

and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(k) Related Information 

(1) For more information about this AD, 

contact Eric Igama, Aerospace Engineer, 

Systems and Equipment Section, FAA, Los 

Angeles ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5388; fax: 562–627–5210; 

email: roderick.igama@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster Blvd., 

MC 110–SK57, Seal Beach, CA 90740–5600; 

telephone 562–797–1717; Internet https://

www.myboeingfleet.com. You may view this 

referenced service information at the FAA, 

Transport Standards Branch, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on August 

16, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–17839 Filed 8–24–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0778; Product 

Identifier 2017–NM–038–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 757–200 

series airplanes. This proposed AD was 

prompted by an evaluation by the 

design approval holder (DAH) 

indicating that the side panel-to-frame 

attachments and frames of the aft cargo 

compartment are subject to widespread 

fatigue damage (WFD). This proposed 

AD would require an inspection of the 

side panel-to-frame attachments and 

frames to verify that certain 

modifications have been done, and 

applicable on-condition actions. We are 

proposing this AD to address the unsafe 

condition on these products. 

DATES: We must receive comments on 

this proposed AD by October 10, 2017. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster 

Blvd., MC 110–SK57, Seal Beach, CA 

90740–5600; telephone 562–797–1717; 

Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Standards Branch, 

1601 Lind Avenue SW., Renton, WA. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2017–0778. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0778; 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: 

Muoi Vuong, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles 

ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5205; fax: 562–627– 

5210; email: Muoi.Vuong@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2017–0778; Product Identifier 2017– 

NM–038–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 

Fatigue damage can occur locally, in 

small areas or structural design details, 

or globally, in widespread areas. 

Multiple-site damage is widespread 

damage that occurs in a large structural 

element such as a single rivet line of a 


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Federal Register / Vol. 82, No. 164 / Friday, August 25, 2017 / Proposed Rules 40509 

lap splice joining two large skin panels. 

Widespread damage can also occur in 

multiple elements such as adjacent 

frames or stringers. Multiple-site 

damage and multiple-element damage 

cracks are typically too small initially to 

be reliably detected with normal 

inspection methods. Without 

intervention, these cracks will grow, 

and eventually compromise the 

structural integrity of the airplane. This 

condition is known as widespread 

fatigue damage. It is associated with 

general degradation of large areas of 

structure with similar structural details 

and stress levels. As an airplane ages, 

WFD will likely occur, and will 

certainly occur if the airplane is 

operated long enough without any 

intervention. 

The FAA’s WFD final rule (75 FR 

69746, November 15, 2010) became 

effective on January 14, 2011. The WFD 

rule requires certain actions to prevent 

structural failure due to WFD 

throughout the operational life of 

certain existing transport category 

airplanes and all of these airplanes that 

will be certificated in the future. For 

existing and future airplanes subject to 

the WFD rule, the rule requires that 

DAHs establish a limit of validity (LOV) 

of the engineering data that support the 

structural maintenance program. 

Operators affected by the WFD rule may 

not fly an airplane beyond its LOV, 

unless an extended LOV is approved. 

The WFD rule (75 FR 69746, 

November 15, 2010) does not require 

identifying and developing maintenance 

actions if the DAHs can show that such 

actions are not necessary to prevent 

WFD before the airplane reaches the 

LOV. Many LOVs, however, do depend 

on accomplishment of future 

maintenance actions. As stated in the 

WFD rule, any maintenance actions 

necessary to reach the LOV will be 

mandated by airworthiness directives 

through separate rulemaking actions. 

In the context of WFD, this action is 

necessary to enable DAHs to propose 

LOVs that allow operators the longest 

operational lives for their airplanes, and 

still ensure that WFD will not occur. 

This approach allows for an 

implementation strategy that provides 

flexibility to DAHs in determining the 

timing of service information 

development (with FAA approval), 

while providing operators with certainty 

regarding the LOV applicable to their 

airplanes. 

Any frame crack at the attachment 

points of the side panel-to-frame 

attachments of the aft cargo 

compartment could go undetected and 

grow in length. This condition could 

result in reduced structural integrity of 

the body frames, and consequent rapid 

decompression of the airplane. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 757–53A0012, Revision 1, 

dated January 25, 2017. The service 

information describes procedures for a 

general visual inspection of the side 

panel-to-frame attachments and frames 

to verify that certain modifications have 

been done. The service information also 

describes procedures for on-condition 

actions, which include repetitive 

inspections for cracking, repairs, and 

modifications. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishment of the actions 

identified as ‘‘RC’’ (required for 

compliance) in the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin 757–53A0012, Revision 1, 

dated January 25, 2017, described 

previously, except for any differences 

identified as exceptions in the 

regulatory text of this proposed AD. 

For information on the procedures 

and compliance times, see this service 

information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0778. 

Explanation of Compliance Time 

The compliance time for the 

replacement specified in this proposed 

AD for addressing WFD was established 

to ensure that discrepant structure is 

replaced before WFD develops in 

airplanes. Standard inspection 

techniques cannot be relied on to detect 

WFD before it becomes a hazard to 

flight. We will not grant any extensions 

of the compliance time to complete any 

AD-mandated service bulletin related to 

WFD without extensive new data that 

would substantiate and clearly warrant 

such an extension. 

Costs of Compliance 

We estimate that this proposed AD 

affects 13 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 

General visual inspection ................................ 1 work-hour × $85 per hour = $85 ................. $0 $85 $1,105 

We estimate the following costs to do 

any necessary on-condition actions that 

would be required. We have no way of 

determining the number of aircraft that 

might need these on-condition actions. 

ESTIMATED COSTS OF ON-CONDITION ACTIONS * 

Labor cost Parts cost Cost per 

product 

Up to 45 work-hours × $85 per hour = Up to $3,825 ..................................................................... Unavailable ................ Up to $3,825. 

* The costs in the table do not include the cost estimate for on-condition repairs. We have received no definitive data that would enable us to 

provide cost estimates for the on-condition repairs specified in this proposed AD. 


pmangrum on DSK3GDR082PROD with PROPOSALS
40510 Federal Register / Vol. 82, No. 164 / Friday, August 25, 2017 / Proposed Rules 

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. 

This proposed AD is issued in 

accordance with authority delegated by 

the Executive Director, Aircraft 

Certification Service, as authorized by 

FAA Order 8000.51C. In accordance 

with that order, issuance of ADs is 

normally a function of the Compliance 

and Airworthiness Division, but during 

this transition period, the Executive 

Director has delegated the authority to 

issue ADs applicable to transport 

category airplanes to the Director of the 

System Oversight Division. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2017–0778; Product Identifier 2017– 

NM–038–AD. 

(a) Comments Due Date 

We must receive comments by October 10, 

2017. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 757–200 series airplanes, certificated 

in any category, as identified in Boeing Alert 

Service Bulletin 757–53A0012, Revision 1, 

dated January 25, 2017. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder indicating that 

the side panel-to-frame attachments and 

frames of the aft cargo compartment are 

subject to widespread fatigue damage. We are 

issuing this AD to prevent fatigue cracking at 

the attachment points of the side panel-toframe attachments of the aft cargo 

compartment, which could result in reduced 

structural integrity of the body frames, and 

consequent rapid decompression of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) One-Time General Visual Inspection and 

Corrective Actions 

Except as required by paragraph (h) of this 

AD: At the applicable times specified in 

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

Alert Service Bulletin 757–53A0012, 

Revision 1, dated January 25, 2017, do all 

applicable actions identified as ‘‘RC’’ 

(required for compliance) in, and in 

accordance with, the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–53A0012, Revision 1, dated January 25, 

2017. 

(h) Exceptions to Service Information 

Specifications 

(1) For purposes of determining 

compliance with the requirements of this AD, 

the phrase ‘‘the effective date of this AD’’ 

may be substituted for ‘‘the Revision 1 date 

of this service bulletin,’’ as specified in 

Boeing Alert Service Bulletin 757–53A0012, 

Revision 1, dated January 25, 2017. 

(2) Where Boeing Alert Service Bulletin 

757–53A0012, Revision 1, dated January 25, 

2017, specifies contacting Boeing, and 

specifies that action as RC: This AD requires 

using a method approved in accordance with 

the procedures specified in paragraph (j) of 

this AD. 

(i) Terminating Action for Inspections 

Accomplishment of a modification in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–53A0012, Revision 1, dated January 25, 

2017, terminates the inspections required by 

paragraph (g) of this AD at the modified 

location only. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles ACO Branch, 

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 

certification office, send it to the attention of 

the person identified in paragraph (k)(1) of 

this AD. Information may be emailed to: 9- 

ANM-LAACO-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, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO Branch, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) Except as required by paragraph (h)(2) 

of this AD: For service information that 

contains steps that are labeled as RC, the 

provisions of paragraphs (j)(4)(i) and (j)(4)(ii) 

of this AD apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. If a step or substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. An AMOC is required for any 

deviations to RC steps, including substeps 

and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 


pmangrum on DSK3GDR082PROD with PROPOSALS
Federal Register / Vol. 82, No. 164 / Friday, August 25, 2017 / Proposed Rules 40511 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(k) Related Information 

(1) For more information about this AD, 

contact Muoi Vuong, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles ACO 

Branch, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5205; fax: 562–627–5210; email: 

Muoi.Vuong@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster Blvd., 

MC 110–SK57, Seal Beach, CA 90740–5600; 

telephone 562–797–1717; Internet https://

www.myboeingfleet.com. You may view this 

referenced service information at the FAA, 

Transport Standards Branch, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on August 

10, 2017. 

Dionne Palermo, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–17538 Filed 8–24–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0779; Product 

Identifier 2017–NM–040–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 787–8 

airplanes. This proposed AD was 

prompted by reports of degraded bondline performance of co-bonded upper 

wing stringer-to-skin joints. This 

proposed AD would require repetitive 

inspections of certain upper wing 

stringers for any disbond and corrective 

actions, if necessary; and a terminating 

preventative modification of installing 

disbond arrestment (DBA) fasteners. 

This proposed AD would also require 

revising the inspection or maintenance 

program to incorporate an airworthiness 

limitation. We are proposing this AD to 

address the unsafe condition on these 

products. 

DATES: We must receive comments on 

this proposed AD by October 10, 2017. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster 

Blvd., MC 110–SK57, Seal Beach, CA 

90740–5600; telephone 562–797–1717; 

Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Standards Branch, 

1601 Lind Avenue SW., Renton, WA. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2017–0779. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0779; 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: 

Allen Rauschendorfer, Aerospace 

Engineer, Airframe Branch, FAA, Seattle 

ACO Branch, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425– 

917–6487; fax: 425–917–6590; email: 

allen.rauschendorfer@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2017–0779; Product Identifier 2017– 

NM–040–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We have received reports of degraded 

bond-line performance of co-bonded 

upper wing stringer-to-skin joints. The 

co-bonded upper wing stringer-to-skin 

joints were determined to have 

degraded bond-line performance due to 

the exposure of the bond surface with 

the use of BMS 8–308 peel ply to cure 

times that exceeded 4 hours at a 

temperature of 345 degrees Fahrenheit 

(F) plus or minus 10 F. The upper wing 

stringer-to-skin joint disbonding can 

reduce the structural capability to where 

it cannot sustain limit load, which 

could adversely affect the structural 

integrity of the airplane. 

Related Service Information Under 1 

CFR Part 51 

We have reviewed Boeing Alert 

Service Bulletin B787–81205– 

SB570030–00, Issue 001, dated March 

17, 2017 (‘‘ASB B787–81205– 

SB570030–00, Issue 001’’). This service 

information describes procedures for 

inspection of certain upper wing 

stringers for any disbond and repairs; 

and for a preventative modification 

which consists of, depending on 

airplane configuration, applying copper 

foil to the upper wing at certain stringer 

and rib bay locations, installing DBA 

fasteners on the upper flanges of the 

upper wing stringers at the stringer and 

rib bay locations, applying cap seals to 

the DBA fasteners, and applying edge 

sealant to the stringers at the DBA 

fastener installation locations. 

We have also reviewed Airworthiness 

Limitation (AWL) 57–AWL–13, 

‘‘Inspection Requirements for In-Tank 

Fasteners and Edge Seal near Disbond 

Arrestment (DBA) Fastener Installations 

of Lightning Zone 2,’’ of Boeing 787 

Special Compliance Items/ 

Airworthiness Limitations, D011Z009– 

03–04, dated February 2017. This 

service information describes tasks for 

inspecting in-tank fasteners and edge 

seals near DBA fastener installations of 

lightning zone 2. 


pmangrum on DSK3GDR082PROD with PROPOSALS